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Diminutive Assembly for Nanosatellite deploYables (DANY) Miniature Release Mechanism

New deployment mechanism offers improved reliability with minimum space and weight penalty. Goddard Space Flight Center, Greenbelt, Maryland CubeSat appendices such as solar panels and antennas often need to be constrained by a release mechanism during launch. These appendices are then deployed once the desired orbit is reached. The usual constraint method used is a combination of an unpredictable/ unreliable fishing line and burning wire. If a proper release mechanism is used, it utilizes a considerable amount of CubeSat internal space, making the internal packaging of the satellite more difficult. These two methods have adverse effects on CubeSat performance.

Posted in: Briefs, TSP

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Quantitative Real-Time Flow Visualization Technique

This technique enables real-time monitoring of pressure fields and flow measurement. John H. Glenn Research Center, Cleveland, Ohio There is a need for experimental techniques that have low cost and rapid turnaround. It is also necessary to obtain quantitative information from such a method. Previous methods are either lacking in quantitative information such as dye or smoke injection, or require considerable set-up and cost such as PIV (particle image velocimetry). A method was developed for visualizing the pressure contours for a turbine cascade in real time to enable rapid evaluation of new concepts. A method for quantitative 3D flow visualization also was developed.

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Thin-Film Evaporative Cooling for Side-Pumped Lasers

This technology has applications in advanced lidar systems for weather satellites; in welding, cutting, and marking; and in test and measurement. Langley Research Center, Hampton, Virginia A highly efficient way to cool solid-state crystal lasers was developed. This thin-film evaporative cooling technique offers higher optical efficiencies and monochromatic quality than traditional conductive cooling techniques. Developed for use in side-pumped 2.0- micron laser systems used in light detection and ranging (lidar) instruments, the thin-film cooling design concept also has broad utility for diode-pumped solid-state laser (DPSSL) systems, especially those with high heat flux or challenging packaging requirements.

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Planar and Non-Planar Multi-Bifurcating Stacked Radial Diffusing Valve Cages

This technology is applicable in systems and devices where high-pressure-differential valves are used. NASA’s Jet Propulsion Laboratory, Pasadena, California A valve cage consists of a stackable planar structure design with paths that are azimuthally cut out and connected radially. The pattern causes the flow to move azimuthally and impinge on each other when moving to the next path, thereby reducing the fluid momentum and energy that reduces the erosion capability. The maze-like structure is easy to machine with standard machining techniques.

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ACS Anchor Guide Stud and Caddy

Goddard Space Flight Center, Greenbelt, Maryland An alignment guide and a mounting interface for two of the repair tools on orbit during the Hubble Space Telescope Servicing Mission 4 (see http://asd.gsfc.nasa.gov/archive/hubble/missions/sm4.html) were developed. This design can be installed in a timely manner, and was specifically developed for a worksite with minimal access and minimal visual line-of-sight to the worksite. In addition, this technology was specifically designed for on-orbit work by astronauts, and can be used for any space-related work where an alignment aid or mounting interface is required.

Posted in: Briefs, TSP, Fastening, Joining & Assembly

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Next-Generation, Lightweight Hard Upper Torso/Hatch Assembly

Lyndon B. Johnson Space Center, Houston, Texas The current MK-III carbon-graphite/epoxy Hard Upper Torso (HUT)/hatch assembly represented an 8.3 psi (≈57 kPa) technology demonstrator model of a zero pre-breathe suit. In this configuration, the MK-III suit weighed about 120 lb (≈54 kg). Since future lunar/planetary suits will need to operate under the influence of gravity, as well as operate at 4.3 psi (≈30 kPa), the weight of the suit had to be reduced to a minimum of 79 lb (≈36 kg) with the incorporation of lightweight structural materials and slight HUT/hatch assembly geometric redesign.

Posted in: Briefs, TSP

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Elastic Deployable Composite Tubular Roll-Out Boom

Goddard Space Flight Center, Greenbelt, Maryland The objective of this work was to develop an innovative deployable boom/structure technology that is ultra-lightweight (<30-grams/meter potential), and has extremely compact stowage volume (>100:1 compaction ratio), broad scalability (no size limits envisioned), high deployed frequency, high deployed strength, good thermal/dimensional stability, reliable/immediate and repeatable controlled deployment, high stiffness maintained during the entire deployment sequence, affordability (simple, easily produced tubular structure, very low parts count, and proven tube manufacture provides low cost and rapid assembly), space environmental survivability, and broad mission applicability.

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