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  • 1
    Publication Date: 2020-01-13
    Description: No abstract available
    Keywords: Spacecraft Design, Testing and Performance
    Type: JPL-CL-16-3842 , IFAC Symposium on Automatic Control in Aerospace; Aug 21, 2016 - Aug 25, 2016; Sherbrooke, Quebec; Canada
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  • 2
    Publication Date: 2019-07-13
    Description: NASA/JPL 's Mars Exploration Rovers acquire their attitude upon command and autonomously propagate their attitude and position. The rovers use accelerometers and images of the sun to acquire attitude, autonomously searching the sky for the sun with a pointable camera. To propagate the attitude and position the rovers use either accelerometer and gyro readings or gyro readings and wheel odometiy, depending on the nature of the movement ground operators are commanding. Where necessary, visual odometry is performed on images to fine tune the position updates, particularly in high slip environments. The capability also exists for visual odometry attitude updates. This paper describes the techniques used by the rovers to acquire and maintain attitude and position knowledge, the accuracy which is obtainable, and lessons learned after more than one year in operation.
    Keywords: Lunar and Planetary Science and Exploration
    Type: IEEE Systems, Man and Cybernetics, International Conference; Oct 09, 2005 - Oct 12, 2005; Waikoloa, HI; United States
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  • 3
    Publication Date: 2019-07-13
    Description: This paper discusses how system validation challenges influenced the design of the EDL architecture and highlights how some of the remaining challenges will be addressed to assure a successful landing of this unprecedented rover on Mars.
    Keywords: Lunar and Planetary Science and Exploration
    Type: IEEE Aerospace Conference; Mar 04, 2006 - Mar 11, 2006; Big Sky, MT; United States
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  • 4
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Space Sciences (General); Space Transportation and Safety
    Type: JSC-CN-31109 , AIAA SpaceOps 2014; May 05, 2014 - May 09, 2014; Pasadena, CA; United States
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  • 5
    Publication Date: 2019-07-13
    Description: The Powered Flight segment of Mars Science Laboratory's (MSL) Entry, Descent, and Landing (EDL) system extends from backshell separation through landing. This segment is responsible for removing the final 0.1% of the kinetic energy dissipated during EDL and culminating with the successful touchdown of the rover on the surface of Mars. Many challenges exist in the Powered Flight segment: extraction of Powered Descent Vehicle from the backshell, performing a 300m divert maneuver to avoid the backshell and parachute, slowing the descent from 85 m/s to 0.75 m/s and successfully lowering the rover on a 7.5m bridle beneath the rocket-powered Descent Stage and gently placing it on the surface using the Sky Crane Maneuver. Finally, the nearly-spent Descent Stage must execute a Flyaway maneuver to ensure surface impact a safe distance from the Rover. This paper provides an overview of the powered flight design, key features, and event timeline. It also summarizes Curiosity's as flown performance on the night of August 5th as reconstructed by the flight team.
    Keywords: Spacecraft Design, Testing and Performance; Lunar and Planetary Science and Exploration
    Type: AAS 13-424 , AAS/AIAA Spaceflight Mechanics Meeting; Feb 10, 2013 - Feb 14, 2013; Kauai, HI; United States
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  • 6
    Publication Date: 2019-07-13
    Description: A deep-space mission has been proposed to redirect an asteroid to a distant retrograde orbit around the moon using a robotic vehicle, the Asteroid Redirect Vehicle (ARV). In this orbit, astronauts will rendezvous with the ARV using the Orion spacecraft. The integrated attitude control concept that Orion will use for approach and docking and for mated operations will be described. Details of the ARV's attitude control system and its associated constraints for redirecting the asteroid to the distant retrograde orbit around the moon will be provided. Once Orion is docked to the ARV, an overall description of the mated stack attitude during all phases of the mission will be presented using a coordinate system that was developed for this mission. Next, the thermal and power constraints of both the ARV and Orion will be discussed as well as how they are used to define the optimal integrated stack attitude. Lastly, the lighting and communications constraints necessary for the crew's extravehicular activity planned to retrieve samples from the asteroid will be examined. Similarly, the joint attitude control strategy that employs both the Orion and the ARV attitude control assets prior, during, and after each extravehicular activity will also be thoroughly discussed.
    Keywords: Space Sciences (General); Space Transportation and Safety
    Type: JSC-CN-30896 , SpaceOps 2014; May 05, 2014 - May 09, 2014; Pasadena, CA; United States
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  • 7
    Publication Date: 2019-12-20
    Description: Europa, the smallest of Jupiters Galilean moons, is thought to harbor a vast liquid water ocean beneath its icy crust, making it one of the most scientifically intriguing targets for a robotic surface sampling mission in our Solar System. However, autonomously landing a spacecraft safely and precisely on Europa poses unique challenges, such as very little existing high-resolution reconnaissance imagery, a surface expected to be very rough and hazardous over a wide range of scales, an extremely intense ionizing radiation environment, and very limited lander resources for mass and volume. To address these challenges, we propose a novel Intelligent Landing System (ILS) combining four Guidance, Navigation & Control (GN&C) sensing functions velocimetry, altimetry, map-relative localization, and hazard detection that would together enable safe and precise landing on Europas surface. The ILS is a smart sensor system, combining an inertial measurement unit (IMU), a monocular, passive-optical camera, and a light detection and ranging (Li-DAR) sensor with dedicated computing resources as well as an onboard 3D terrain map. The ILS leverages more than a decade of technology development from programs such as the Lander Vision System, currently baselined on the Mars 2020 mission. This paper provides a detailed description of the proposed ILS architecture and concept of operations, as well as select preliminary simulation results to assess performance and robustness.
    Keywords: Spacecraft Design, Testing and Performance
    Type: JPL-CL-CL#17-0517 , Annual Guidance and Control Conference; Feb 02, 2017 - Feb 08, 2017; Breckenridge, CO; United States
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  • 8
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Spacecraft Design, Testing and Performance
    Type: International Planetary Probe (IPPW-8) Workshop; Jun 06, 2011 - Jun 10, 2011; Norfolk, VA; United States
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  • 9
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Spacecraft Design, Testing and Performance
    Type: International ESA Conference on Guidance and Navigation Control Systems; Jun 05, 2011 - Jun 10, 2011; Carlsbad; Czechoslovakia
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