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  • Cybernetics, Artificial Intelligence and Robotics  (4)
  • Spacecraft Design, Testing and Performance  (2)
  • Aerodynamics; Spacecraft Design, Testing and Performance  (1)
  • Chalcone synthase  (1)
  • Electronics and Electrical Engineering  (1)
  • FABRICATION TECHNOLOGY  (1)
Collection
Keywords
Publisher
Years
  • 1
    Electronic Resource
    Electronic Resource
    Analysis of the parsley chalcone-synthase promoter in response to different light qualities (1994)
    Springer
    Planta 193 (1994), S. 275-282 
    Details
    ISSN: 1432-2048
    Keywords: Chalcone synthase ; Footprinting in vivo ; Gene expression (transient) ; Light regulation (UV-B photoreceptor, blue-light photoreceptor) ; Petroselinum
    Source: Springer Online Journal Archives 1860-2000
    Topics: Biology
    Notes: Abstract We examined the chalcone synthase (chs) promoter from parsley [Petroselinum crispum Miller (A.W. Hill)] for the existence of separate promoter elements responsible for transcriptional activation of the chs gene by UV-B and by blue light. A combination of in-vivo footprinting in parsley cells and light-induced transient expression assays with different chs promoter constructs in parsley protoplasts was used. Dark controls and bluelight-irradiated cells gave identical in-vivo footprints on the chs promoter. Pre-irradiation with blue light prior to a UV-B-light pulse is known to cause a shift in the timing of UV-B-light-induced increase in chs transcription rates. This shift was also manifested on the DNA template, since UV-B-light-induced in-vivo footprints in cells pretreated with blue light were detected earlier than in cells which had been irradiated with a UV-B-light pulse only. Although there was a clear shift in the timing of footprint appearance, the patterns of footprinting did not change. Light-induced transient-expression assays revealed that the shortest tested chs promoter which retained any light responsiveness, was sufficient for mediating both induction by UV light and the blue-light-mediated kinetic shift. These findings argue against a spatial separation of UV-B- and blue-light-responsive elements on the chs promoter. We interpret these data by postulating that the signal transduction pathways originating from the excitation of UV-B- and blue-light receptors merge at the chs promoter, or somewhere between light perception and protein-DNA interaction.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00192541
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Experimental Results for Titan Aerobot Thermo-Mechanical Subsystem Development (2006)
    In:  Other Sources
    Details
    Publication Date: 2018-06-11
    Description: This paper presents experimental results on a set of 4 thermo-mechanical research tasks aimed at Titan and Venus aerobots: 1. A cryogenic balloon materials development program culminating in the fabrication and testing of a 4.6 m long blimp prototype at 93K. 2. A combined computational and experimental thermal analysis of the effect of radioisotope power system (RPS) waste heat on the behavior of a helium filled blimp hull. 3. Aerial deployment and inflation testing using a blimp 4. A proof of concept experiment with an aerobot-mounted steerable high gain antenna These tasks were supported with JPL internal R&D funds and executed by JPL engineers with substantial industry collaboration for Task #1, the cryogenic balloon materials
    Keywords: Cybernetics, Artificial Intelligence and Robotics
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Ultra Lightweight Ballutes for Return to Earth from the Moon (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Ultra lightweight ballutes offer revolutionary mass and cost benefits along with flexibility in flight system design compared to traditional entry system technologies. Under funding provided by NASA s Exploration Systems Research & Technology program, our team was able to make progress in developing this technology through systems analysis and design, evaluation of materials and construction methods, and development of critical analysis tools. Results show that once this technology is mature, significant launch mass savings, operational simplicity, and mission robustness will be available to help carry out NASA s Vision for Space Exploration.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA Paper 2006-1698 , 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; May 01, 2006 - May 04, 2006; Newport, RI; United States
    Format: application/pdf
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  • 4
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    Autonomous flight control for a Titan exploration aerobot (2005)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In this paper, we discuss steps towards the development of an autonomy architecture, and concentrate on the autonomous flight control subsystem.
    Keywords: Cybernetics, Artificial Intelligence and Robotics
    Type: Robotics Science and Systems; Jun 08, 2005 - Jun 11, 2005; Cambridge, MA; United States
    Format: text
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  • 5
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    An aerobot for global in situ exploration of Titan (2004)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the design and component testing of an aerobot that would be capable of global in situ exploration of Saturn's moon, Titan, over a 6 to 12 month mission lifetime. The proposed aerobot is a propeller-driven, buoyant vehicle that resembles terrestrial airships. However, the extremely cold Titan environment requires the use of cryogenic materials of construction and careful thermal design for protection of temperature-sensitive payload elements. Multiple candidate balloon materials have been identified based on extensive laboratory testing at 77 K. The most promising materials to date are laminates comprised of polyester fabrics and/or films with areal densities in the range of 40-100 g/m2. The aerobot hull is a streamlined ellipsoid 14 meters in length with a maximum diameter of 3 meters. The enclosed volume of 60 m3 is sufficient to float a mass of 234 kg at a maximum altitude of 8 km at Titan. Forward and aft ballonets are located inside the hull to enable the aerobot to descend to the surface while preserving a fully inflated streamlined shape. Altitude changes are effected primarily through thrust vectoring of the twin main propellers, with pressure modulated buoyancy change via the ballonets available as a slower backup option. A total of 100 W of electrical power is provided to the vehicle by a radioisotope power supply. Up to half of this power is available to the propulsion system to generate a top flight speed in the range of 1-2 m/s. This speed is expected to be greater than the near surface winds at Titan, enabling the aerobot to fly to and hover over targets of interest. A preliminary science payload has been devised for the aerobot to give it the capability for aerial imaging of the surface, atmospheric observations and sampling, and surface sample acquisition and analysis. Targeting, hovering, surface sample acquisition and vehicle health monitoring and automatic safing actions will all require significant on-board autonomy due to the over two hour round trip light time between Titan and Earth. An autonomy architecture and a core set of perception, reasoning and control technologies is under development using a free-flying airship testbed of approximately the same size as the proposed Titan aerobot. Data volume from the Titan science mission is expected to be on the order of 100-300 Mbit per day transmitted either direct to Earth through an 0.8 m high gain antenna or via an orbiter relay using an omni-directional antenna on the aerobot.
    Keywords: Cybernetics, Artificial Intelligence and Robotics
    Type: 35th Committee on Space Research (COSPAR) Scientific Assembly; Jul 18, 2004 - Jul 25, 2004; Paris; France
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Rolling Stitch Welder For Foil (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Hand-operated rolling spotwelder stitch-welds foil faster and more consistently than single-spotwelding gun without damaging it. Internal spring reacts against roller frame, exerting force on welding wheel when rollers contact workpiece.
    Keywords: FABRICATION TECHNOLOGY
    Type: MFS-29740 , NASA Tech Briefs (ISSN 0145-319X); 16; 6; P. 79
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  • 7
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    Aerocapture Systems Analysis for a Neptune Mission (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A Systems Analysis was completed to determine the feasibility, benefit and risk of an aeroshell aerocapture system for Neptune and to identify technology gaps and technology performance goals. The systems analysis includes the following disciplines: science; mission design; aeroshell configuration; interplanetary navigation analyses; atmosphere modeling; computational fluid dynamics for aerodynamic performance and aeroheating environment; stability analyses; guidance development; atmospheric flight simulation; thermal protection system design; mass properties; structures; spacecraft design and packaging; and mass sensitivities. Results show that aerocapture is feasible and performance is adequate for the Neptune mission. Aerocapture can deliver 1.4 times more mass to Neptune orbit than an all-propulsive system for the same launch vehicle and results in a 3-4 year reduction in trip time compared to all-propulsive systems. Enabling technologies for this mission include TPS manufacturing; and aerothermodynamic methods for determining coupled 3-D convection, radiation and ablation aeroheating rates and loads.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA/TM-2006-214300 , L-19236
    Format: application/pdf
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  • 8
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    Flow Energy Piezoelectric Bimorph Nozzle Harvester (2014)
    In:  Other Sources
    Details
    Publication Date: 2019-08-26
    Description: There is a need for a long-life power generation scheme that could be used downhole in an oil well to produce 1 Watt average power. There are a variety of existing or proposed energy harvesting schemes that could be used in this environment but each of these has its own limitations. The vibrating piezoelectric structure is in principle capable of operating for very long lifetimes (decades) thereby possibly overcoming a principle limitation of existing technology based on rotating turbo-machinery. In order to determine the feasibility of using piezoelectrics to produce suitable flow energy harvesting, we surveyed experimentally a variety of nozzle configurations that could be used to excite a vibrating piezoelectric structure in such a way as to enable conversion of flow energy into useful amounts of electrical power. These included reed structures, spring mass-structures, drag and lift bluff bodies and a variety of nozzles with varying flow profiles. Although not an exhaustive survey we identified a spline nozzle/piezoelectric bimorph system that experimentally produced up to 3.4 mW per bimorph. This paper will discuss these results and present our initial analyses of the device using dimensional analysis and constitutive electromechanical modeling. The analysis suggests that an order-of-magnitude improvement in power generation from the current design is possible.
    Keywords: Electronics and Electrical Engineering
    Type: SPIE Smart Structures and Non-Destructive Evaluation; Mar 09, 2014 - Mar 13, 2014; San Diego, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    An Autonomy Architecture for Aerobot Exploration of the Saturnian Moon Titan (2008)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Huygens probe arrived at Saturn's moon Titan on January 14, 2005, unveiling a world that is radically different from any other in the Solar system. The data obtained, complemented by continuing observations from the Cassini spacecraft, show methane lakes, river channels and drainage basins, sand dunes, cryovolcanos and sierras. This has lead to an enormous scientific interest in a follow-up mission to Titan, using a robotic lighter-than-air vehicle (or aerobot). Aerobots have modest power requirements, can fly missions with extended durations, and have very long distance traverse capabilities. They can execute regional surveys, transport and deploy scientific instruments and in-situ laboratory facilities over vast distances, and also provide surface sampling at strategic science sites. This paper describes our progress in the development of the autonomy technologies that will be required for exploration of Titan. We provide an overview of the autonomy architecture and some of its key components. We also show results obtained from autonomous flight tests conducted in the Mojave desert.
    Keywords: Cybernetics, Artificial Intelligence and Robotics
    Type: IEEEAC Paper 1296 , IEEE Aerospace 2008; Mar 01, 2008; Big Sky, MT; United States
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    NASA TECHNICAL REPORTS
  • 10
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    A Survey of Titan Balloon Concepts and Technology Status (2011)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper surveys the options for, and technology status of, balloon vehicles to explore Saturn's moon Titan. A significant amount of Titan balloon concept thinking and technology development has been performed in recent years, particularly following the spectacular results from the descent and landing of the Huygens probe and remote sensing observations by the Cassini spacecraft. There is widespread recognition that a balloon vehicle on the next Titan mission could provide an outstanding and unmatched capability for in situ exploration on a global scale. The rich variety of revealed science targets has combined with a highly favorable Titan flight environment to yield a wide diversity of proposed balloon concepts. The paper presents a conceptual framework for thinking about balloon vehicle design choices and uses it to analyze various Titan options. The result is a list of recommended Titan balloon vehicle concepts that could perform a variety of science missions, along with their projected performance metrics. Recent technology developments for these balloon concepts are discussed to provide context for an assessment of outstanding risk areas and technological maturity. The paper concludes with suggestions for technology investments needed to achieve flight readiness.
    Keywords: Aerodynamics; Spacecraft Design, Testing and Performance
    Type: AIAA Balloon Systems Conference; Sep 20, 2011 - Sep 22, 2011; Virginia Beach, VA; United States
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