2 edition of Test and evaluate passive orbital disconnect struts (PODS-III) found in the catalog.
Test and evaluate passive orbital disconnect struts (PODS-III)
by National Aeronautics and Space Administration, Ames Research Center, National Technical Information Service, distributor in Moffett Field, Calif, [Springfield, Va
Written in English
|Statement||R.T. Parmley ... [et al.]|
|Series||NASA contractor report -- 177368, NASA contractor report -- NASA CR-177368|
|Contributions||Parmley, R. T, Ames Research Center|
|The Physical Object|
The orbitals are described completely by specifying three quantum numbers, but only two are used in this book. The principal quantum number (symbolized n) is a whole number, 1 or greater, that identifies the main energy shell of the orbital, with 1 being closest to the nucleus and each subsequent level farther from the second quantum number, known as the azimuthal quantum number. Long Term Cryogen Storage in Space: A Feasibility Study.- Sintered Plug Flow Modulation of a Vapor-Liquid Phase Separator for a Helium II Vessel.- Superfluid Porous Plug Performance.- Zero-g Experiments with a He II Active Phase Separator for Space Application.- Passive Orbital Disconnect .
The Common Berthing Mechanism (CBM) connects habitable elements in the US Orbital Segment (USOS) of the International Space Station (ISS). The CBM has two distinct sides that, once mated, form a cylindrical vestibule between modules. The vestibule is about . A passive thermal control system helps maintain the temperature of the orbiter spacecraft, systems and components within their temperature limits. Orbiter Purge, Vent and Drain System The purge, vent and drain system on the orbiter is designed to prevent accumulation of hazardous gasses and vent compartments.
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Get this from a library. Test and evaluate passive orbital disconnect struts (PODS-III). [R T Parmley; Ames Research Center.;]. Passive Orbital Disconnect Struts (PODS) can potentially reduce the support conductance a factor of 10 over state-of-the-art tension band nondisconnect supports and can significantly reduce helium dewar weights without reducing lifetime.
A series of thermal and structural tests have demonstrated this performance by: The objectives of the Passive Orbital Disconnect Struts (PODS) test are to evaluate modal resonance of the PODS-III supports to obtain engineering data required for use of PODS-III on flight systems; determine possible performance improvements in large LO2/LH2 space applications.
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Passive orbital disconnect struts can potentially reduce the support conductance a factor of 10 over state-of-the-art tension band nondisconnect supports and cut helium dewar weights in half for the same lifetime. A series of thermal and structural tests were performed to verify that this performance improvement is by: 3.
Abstract. A prior study 1 has shown that the weight of a three-year lifetime superfluid helium dewar is cut in half if passive orbital disconnect strut (PODS) supports are used in place of nondiscon-nect, state-of-the-art, fiberglass-tension-band supports. If the same tank sizes are used, the lifetime is tripled.
This paper discusses the design concept and heat transfer tests with a cold. The support structure for the tanks is a major source of heat leak. After evaluating strut designs, we decided to incorporate passive orbital disconnect struts (PODS). A schematic of a PODS is sketched in Fig.
As shown by the arrows, the heat path in space is through a longer path with a much smaller cross-section area. Abstract. Gravity Probe B is an orbital test of Einstein’s general theory of relativity using gyroscopes.
The precession of the gyroscopes will measure both the geodetic effect ( arc sec/yr) through the curved space-time surrounding the Earth and the motional effect ( arc sec/yr) due to the rotating Earth dragging space-time around with it.
The objectives of the Passive Orbital Disconnect Struts (PODS) test are to evaluate modal resonance of the PODS-III supports to obtain engineering data required for use of PODS-III on flight.
References 1 Parmley, R.T. Passive orbital disconnect struts (PODS III) structural test program, NASA Report, NASA CR(January ) 2 Lee, J.H. and Brooks, W.F. Cryogenic and thermal design for the Space Infrared Telescope Facility J Spacecraft (January ) 3 Hopkins, R.A.
and Rysehkewit~h, M.G. Measured ground performance and. - This design combinesthe desirable features of a thermal disconnect during "; groundhold andorbit with the high reliability of a comp'letelypasstve _ design, Since the struts do not short out tn one-go the orbital performance: of the struts can be demonstratedtn one-gthermal qualification tests and the.
A passive orbital disconnect strut uses overlapped tubes loaded in parallel and can be used when the largest forces occur infrequently for a short duration and the long-term operational forces are much smaller (e.g. the forces acting on a satellite during launch and in orbit).
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Passive orbital disconnect struts can potentially reduce the support conductance a factor of 10 over state-of-the-art tension band nondisconnect supports and cut helium dewar weights in half for.
Concern 1 was met by using PODS Passive Orbital Disconnect Struts developed by Lockheed under a separate NASA contract to provide rigid support under tension or compression, relaxing in low-g.
The actual gain was somewhat less than expected since 6. Colorado Springs, Colorado, spectacularly located at the foot of Pike's Peak, was the site of the joint Cryogenic Engineer ing Conference - International Cryogenic Materials Conference. Over papers were presented at the two conferences on a variety of cryogenic science and engineering.
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Kittel's research works with citations and 1, reads, including: Ultimate Temperature of Pulse Tube Cryocoolers.
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