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  • 1
    Electronic Resource
    Electronic Resource
    Springer
    Autonomous robots 3 (1996), S. 145-168 
    ISSN: 1573-7527
    Keywords: autonomous underwater vehicles ; underwater navigation ; underwater mapping ; elevation maps ; acoustic backscatter ; sidescan sonar ; shape from shading ; seafloor scattering models
    Source: Springer Online Journal Archives 1860-2000
    Topics: Computer Science , Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Abstract Elevation map generation is an essential component of any autonomous underwater vehicle designed to navigate close to the seafloor because elevation maps are used for obstacle avoidance, path planning and self localization. We present an algorithm for the reconstruction of elevation maps of the seafloor from side-scan sonar backscatter images and sparse bathymetric points co-registered within the image. Given the trajectory for the underwater vehicle, the reconstruction is corrected for the attitude of the side-scan sonar during the image generation process. To perform reconstruction, an arbitrary but computable scattering model is assumed for the seafloor backscatter. The algorithm uses the sparse bathymetric data to generate an initial estimate for the elevation map which is then iteratively refined to fit the backscatter image by minimizing a global error functional. Concurrently, the parameters of the scattering model are determined on a coarse grid in the image by fitting the assumed scattering model to the backscatter data. The reconstruction is corrected for the movement of the sensor by initially doing local reconstructions in sensor coordinates and then transforming the local reconstructions to a global coordinate system using vehicle attitude and performing the reconstruction again. We demonstrate the effectiveness of our algorithm on synthetic and real data sets. Our algorithm is shown to decrease the average elevation error when compared to real bathymetry from 4.6 meters for the initial surface estimate to 1.6 meters for the final surface estimate from a survey taken of the Juan de Fuca Ridge.
    Type of Medium: Electronic Resource
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  • 2
    Publication Date: 2013-08-31
    Description: Space science and solar system exploration are driving NASA to develop an array of small body missions ranging in scope from near body flybys to complete sample return. This paper presents an algorithm for onboard motion estimation that will enable the precision guidance necessary for autonomous small body landing. Our techniques are based on automatic feature tracking between a pair of descent camera images followed by two frame motion estimation and scale recovery using laser altimetry data. The output of our algorithm is an estimate of rigid motion (attitude and position) and motion covariance between frames. This motion estimate can be passed directly to the spacecraft guidance and control system to enable rapid execution of safe and precise trajectories.
    Keywords: Astronautics (General)
    Format: application/pdf
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  • 3
    Publication Date: 2019-07-12
    Description: The Autonomous Landing and Hazard Avoidance Technology (ALHAT) program is building a sensor that enables a spacecraft to evaluate autonomously a potential landing area to generate a list of hazardous and safe landing sites. It will also provide navigation inputs relative to those safe sites. The Hazard Detection System Compute Element (HDS-CE) box combines a field-programmable gate array (FPGA) board for sensor integration and timing, with a multicore computer board for processing. The FPGA does system-level timing and data aggregation, and acts as a go-between, removing the real-time requirements from the processor and labeling events with a high resolution time. The processor manages the behavior of the system, controls the instruments connected to the HDS-CE, and services the "heavy lifting" computational requirements for analyzing the potential landing spots.
    Keywords: Man/System Technology and Life Support
    Type: NPO-48786 , NASA Tech Briefs, April 2013; 12-13
    Format: application/pdf
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  • 4
    Publication Date: 2019-07-12
    Description: The purpose of Hazard Relative Navigation (HRN) is to provide measurements to the Navigation Filter so that it can limit errors on the position estimate after hazards have been detected. The hazards are detected by processing a hazard digital elevation map (HDEM). The HRN process takes lidar images as the spacecraft descends to the surface and matches these to the HDEM to compute relative position measurements. Since the HDEM has the hazards embedded in it, the position measurements are relative to the hazards, hence the name Hazard Relative Navigation.
    Keywords: Space Communications, Spacecraft Communications, Command and Tracking
    Type: NPO-47115 , NASA Tech Briefs, October 2011; 29-30
    Format: application/pdf
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  • 5
    Publication Date: 2019-07-13
    Description: Human and robotic planetary lander missions require accurate surface relative position knowledge to land near science targets or next to pre-deployed assets. In the absence of GPS, accurate position estimates can be obtained by automatically matching sensor data collected during descent to an on-board map. The Lander Vision System (LVS) that is being developed for Mars landing applications generates landmark matches in descent imagery and combines these with inertial data to estimate vehicle position, velocity and attitude. This paper describes recent LVS design work focused on making the map relative localization algorithms robust to challenging environmental conditions like bland terrain, appearance differences between the map and image and initial input state errors. Improved results are shown using data from a recent LVS field test campaign. This paper also fills a gap in analysis to date by assessing the performance of the LVS with data sets containing significant vertical motion including a complete data set from the Mars Science Laboratory mission, a Mars landing simulation, and field test data taken over multiple altitudes above the same scene. Accurate and robust performance is achieved for all data sets indicating that vertical motion does not play a significant role in position estimation performance.
    Keywords: Computer Programming and Software; Spacecraft Design, Testing and Performance
    Type: AIAA SciTech 2016; Jan 04, 2016 - Jan 06, 2016; San Diego, CA; United States
    Format: text
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  • 6
    Publication Date: 2019-07-13
    Description: Since 2011, the Autonomous Descent and Ascent Powered-Flight Testbed (ADAPT) has been used to demonstrate advanced descent and landing technologies onboard the Masten Space Systems (MSS) Xombie vertical-takeoff, vertical-landing suborbital rocket. The current instantiation of ADAPT is a stand-alone payload comprising sensing and avionics for terrain-relative navigation and fuel-optimal onboard planning of large divert trajectories, thus providing complete pin-point landing capabilities needed for planetary landers. To this end, ADAPT combines two technologies developed at JPL, the Lander Vision System (LVS), and the Guidance for Fuel Optimal Large Diverts (G-FOLD) software. This paper describes the integration and testing of LVS and G-FOLD in the ADAPT payload, culminating in two successful free flight demonstrations on the Xombie vehicle conducted in December 2014.
    Keywords: Avionics and Aircraft Instrumentation; Spacecraft Design, Testing and Performance
    Type: Annual AIAA Space Conference & Exposition 2015; Aug 31, 2015 - Sep 02, 2015; Pasadena, CA; United States
    Format: text
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  • 7
    Publication Date: 2019-08-28
    Description: Apparatuses, systems, computer programs and methods for performing hazard detection and avoidance for landing vehicles are provided. Hazard assessment takes into consideration the geometry of the lander. Safety probabilities are computed for a plurality of pixels in a digital elevation map. The safety probabilities are combined for pixels associated with one or more aim points and orientations. A worst case probability value is assigned to each of the one or more aim points and orientations.
    Keywords: Electronics and Electrical Engineering
    Format: application/pdf
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  • 8
    Publication Date: 2019-07-13
    Description: Program to Optimize Simulated Trajectories II (POST2) is used as a basis for an end-to-end descent and landing trajectory simulation that is essential in determining design and integration capability and system performance of the lunar descent and landing system and environment models for the Autonomous Landing and Hazard Avoidance Technology (ALHAT) project. The POST2 simulation provides a six degree-of-freedom capability necessary to test, design and operate a descent and landing system for successful lunar landing. This paper presents advances in the development and model-implementation of the POST2 simulation, as well as preliminary system performance analysis, used for the testing and evaluation of ALHAT project system models.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA/AAS Astrodynamics Specialist Conference; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
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  • 9
    Publication Date: 2019-07-13
    Description: This paper presents an optics-based model that simulates the size and optical density of image artifacts produced by dust particles.
    Keywords: Cybernetics, Artificial Intelligence and Robotics
    Type: 8th International Symposium on Artificial Intelligence, Robotics and Automation in Space; Sep 05, 2005 - Sep 09, 2005; Munich; Germany
    Format: text
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  • 10
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Man/System Technology and Life Support
    Type: International Conference on Environmental Systems; Jul 12, 2009 - Jul 16, 2009; Savannah, GA; United States
    Format: text
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