3,195 resources related to Mars
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The conference program will consist of plenary lectures, symposia, workshops and invitedsessions of the latest significant findings and developments in all the major fields of biomedical engineering.Submitted full papers will be peer reviewed. Accepted high quality papers will be presented in oral and poster sessions,will appear in the Conference Proceedings and will be indexed in PubMed/MEDLINE.
The International Conference on Image Processing (ICIP), sponsored by the IEEE SignalProcessing Society, is the premier forum for the presentation of technological advances andresearch results in the fields of theoretical, experimental, and applied image and videoprocessing. ICIP 2020, the 27th in the series that has been held annually since 1994, bringstogether leading engineers and scientists in image and video processing from around the world.
The International Conference on Robotics and Automation (ICRA) is the IEEE Robotics and Automation Society’s biggest conference and one of the leading international forums for robotics researchers to present their work.
The 2020 IEEE International Conference on Systems, Man, and Cybernetics (SMC 2020) will be held in Metro Toronto Convention Centre (MTCC), Toronto, Ontario, Canada. SMC 2020 is the flagship conference of the IEEE Systems, Man, and Cybernetics Society. It provides an international forum for researchers and practitioners to report most recent innovations and developments, summarize state-of-the-art, and exchange ideas and advances in all aspects of systems science and engineering, human machine systems, and cybernetics. Advances in these fields have increasing importance in the creation of intelligent environments involving technologies interacting with humans to provide an enriching experience and thereby improve quality of life. Papers related to the conference theme are solicited, including theories, methodologies, and emerging applications. Contributions to theory and practice, including but not limited to the following technical areas, are invited.
All areas of ionizing radiation detection - detectors, signal processing, analysis of results, PET development, PET results, medical imaging using ionizing radiation
The IEEE Aerospace and Electronic Systems Magazine publishes articles concerned with the various aspects of systems for space, air, ocean, or ground environments.
Experimental and theoretical advances in antennas including design and development, and in the propagation of electromagnetic waves including scattering, diffraction and interaction with continuous media; and applications pertinent to antennas and propagation, such as remote sensing, applied optics, and millimeter and submillimeter wave techniques.
IEEE Antennas and Wireless Propagation Letters (AWP Letters) will be devoted to the rapid electronic publication of short manuscripts in the technical areas of Antennas and Wireless Propagation.
Speech analysis, synthesis, coding speech recognition, speaker recognition, language modeling, speech production and perception, speech enhancement. In audio, transducers, room acoustics, active sound control, human audition, analysis/synthesis/coding of music, and consumer audio. (8) (IEEE Guide for Authors) The scope for the proposed transactions includes SPEECH PROCESSING - Transmission and storage of Speech signals; speech coding; speech enhancement and noise reduction; ...
The theory, design and application of Control Systems. It shall encompass components, and the integration of these components, as are necessary for the construction of such systems. The word `systems' as used herein shall be interpreted to include physical, biological, organizational and other entities and combinations thereof, which can be represented through a mathematical symbolism. The Field of Interest: shall ...
Space Antenna Handbook, None
24th Digital Avionics Systems Conference, 2005
Deep Space Communications, None
The Mars Reconnaissance Orbiter (MRO) mission has the primary objective of placing a science orbiter into a low and near‐circular Sun‐synchronous Mars orbit to perform remote sensing investigations to characterize the surface, subsurface, and atmosphere of the planet and to identify potential landing sites for future missions. This chapter describes the specific telecom calibrations and activities. Aerobraking ended with MRO ...
12th Canadian Symposium on Remote Sensing Geoscience and Remote Sensing Symposium,, 1989
Deep Space Communications, None
This chapter describes and assesses telecommunications of the two rovers launched in 2003 and named Spirit and Opportunity. Generally, the term 'spacecraft' refers to the vehicle before landing, and the term 'rover' refers to the vehicle after landing. For each spacecraft, there were three phases of the Mars Exploration Rover (MER) primary flight mission. The chapter provides a description of ...
Developing a Plasma Thruster in Costa Rica
Robotics History: Narratives and Networks Oral Histories:Brian Wilcox
Synthetic Fuels to the Rescue?
Engineering the Big Bang
IROS TV 2019- How to Build a Robot: Vision Based Estimation of Driving Energy for Planetary Rovers
2015 IEEE Honors: IEEE Dennis J. Picard Medal for Radar Technologies and Applications - Marshall Greenspan
The AcceleGlove: A Cheap and Lightweight Control Glove
The Full Spectrum: COSMIC Satellites Use GPS to Forecast Weather
Visit to the Lightning Lab: Zapping Model Airplanes with Over 2 Million Volts
Demonstrations of Gravity-Independent Mobility and Drilling on Natural Rock using Microspines
Future of Space Exploration from the Leaders at Mars One, Astrobotic, and Teledyne Brown Engineering: Innovation Spotlight with Grant Imahara
The Full Spectrum: Travelogue of the Atomic Age
Conversations at IEEE N3XT 2016: Melissa Marshall
Robotics History: Narratives and Networks Oral Histories:Rich Volpe
Engineering Our Future - Randii R. Wessen, Ph.D
IEEE Risk Management and Professional Liability Program
2013 IEEE Simon Ramo Medal
The Mars Reconnaissance Orbiter (MRO) mission has the primary objective of placing a science orbiter into a low and near‐circular Sun‐synchronous Mars orbit to perform remote sensing investigations to characterize the surface, subsurface, and atmosphere of the planet and to identify potential landing sites for future missions. This chapter describes the specific telecom calibrations and activities. Aerobraking ended with MRO in a slightly elliptical low‐altitude Sun‐synchronous orbit, called the science orbit. The antenna placement on an arriving/descending vehicle and that vehicle's attitudes relative to the orbiter are critical to maintain communication during EDL. The high‐gain antenna (HGA) consists of three main components: the feed, an ellipsoidal subreflector, and a 3‐m offset parabolic main reflector. The Ka‐band demonstration includes an assessment of the DSN's readiness to track Ka‐band signals from deep‐space missions. The MRO test was planned in the form of a telecommunications technology demonstration.
This chapter describes and assesses telecommunications of the two rovers launched in 2003 and named Spirit and Opportunity. Generally, the term 'spacecraft' refers to the vehicle before landing, and the term 'rover' refers to the vehicle after landing. For each spacecraft, there were three phases of the Mars Exploration Rover (MER) primary flight mission. The chapter provides a description of the MER X‐band and UHF telecommunication subsystems, with emphasis on both their development and operational challenges and lessons learned. The MER spacecraft were designed, built, and tested at the Jet Propulsion Laboratory (JPL) in Pasadena, California. The MER Flight Team is located at JPL.MER has been a fantastically successful mission, with both rovers reaching Mars’ surface and embarking on explorations lasting far longer than the full mission‐success criterion of 90 sols each. The chapter discusses the MER telecom operations and performance for the primary mission and the first extended mission.
We discuss the advantages of the conversion of electromagnetic field problems to the Fredholm second-kind integral equations (analytical regularization) and Fredholm second-kind infinite-matrix equations (analytical preconditioning). Special attention is paid to specific features of the characterization of metals and dielectrics in the optical range and their effect on the problem formulation and on the methods applicable to the mentioned conversion.
This chapter is written from the perspective that the Mars Science Laboratory (MSL) spacecraft was launched in 2011; it cruised to Mars; it went through entry, descent, and landing (EDL) in 2012; and the MSL curiosity rover has since operated on the surface of Mars. MSL's initial telecom capability after launch employed a non‐directive low‐gain antenna (LGA) and depended on the spacecraft orientation and the limited distance between Earth and the spacecraft. The chapter contains more detailed information regarding the EDL communications geometry and the rationale behind the 135‐deg orbiter and the 75‐deg Earth angles from the antivelocity vector for relay and DTE coverage. The X‐band subsystem (with DSDST, RSDST, TWTA, and SSPA as the active elements) was primary for cruise through EDL and is also used for DFEs, DTEs, and beeps during surface communications. EDL was a critical and the most anticipated communications mission phase.
Summary form only given. High-performance 5 to 10 kW class ion propulsion technology has been identified as a key requirement and priority for technology development to support the Exploration of the Solar System (ESS) theme of the Space Science Enterprise. Identified applications include Mars missions, Europa Lander, Saturn Ring Observer, Neptune Orbiter, Comet Nucleus Sample and Return, and Venus Surface Sample and Return. To that end, there is an ongoing, effort at NASA Glenn Research Center (GRC) to extend ion thruster technology beyond the 30 cm, 2.3 kW engines developed under the NASA Solar Electric Propulsion Technology Applications Readiness (NSTAR) program. Two prototype (laboratory model) 40 cm, 5 kW ion thrusters were developed using two different discharge chamber geometries to evaluate magnetic field contours and discharge chamber performance. Differences from the nominal NSTAR-type ion thruster include an increase in discharge chamber diameter from 30 to 40 cm, the use of mild steel instead of non-ferrous Al or Ti for the anode, an increase in the number of rings of magnets forming the ring-cusp magnetic field, and, in the case of the purely conical chamber, a significant change in the overall geometry of the discharge chamber. Final magnetic field configurations including comparisons to numerical modeling and initial thruster performance data are presented. The impact of this data on the design of high-fidelity (engineering model) 40 cm, 10 kW thrusters currently being developed at NASA GRC is also discussed.
In this paper, we try to identify and quantify the chemical species present on the surface of planet Mars with the help of hyperspectral images provided by the instrument OMEGA (Bibring et al., 2004). For this purpose, we suppose that the spectrum of each pixel is a linear mixture of the spectra of different endmembers. From this linear mixture hypothesis, our work is divided into two steps. Firstly, we propose a new unsupervised method for estimating the number of endmembers based on the eigenvalues of covariance and correlation matrix of the hyperspectral data. This method is then validated on synthetic data. With the help of the number estimated by the precedent step, we use the vertex component analysis (VCA) to extract the spectra and the abundances of the endmembers. The results on hyperspectral image acquired by the OMEGA instrument are shown.
The JPL/NASA Advanced Technology Demonstration (ATD) Program is planning a Mars Sample Return (MSR) mission circa 2005. This mission will have a rover on Mars to pick and place soil samples into a small spherical canister (16 cm diameter), which will be ejected into Martian orbit and retrieved by an orbiting spacecraft. This spacecraft will than bring the canister back to Earth for sample analysis. During canister ascent toward the orbiting spacecraft, a UHF transponder/beacon transmitt/receive signal is needed from the canister. This calls for a miniaturized low-profile antenna with an omni- directional pattern to be mounted onto the outer skin of the small canister. Antenna miniaturization techniques used on this circular patch are two fold: high dielectric-constant substrate material and multiple slats on the patch. This paper presents an antenna that combines these two techniques with dual- frequency and dual-polarization capabilities. The radiation characteristics of this antenna, when mounted on the small canister, as well as on flat ground planes of various sizes, are discussed. The bandwidth and efficiency performance and thermal effect of this antenna are also presented. In general, the antenna radiates a nearly omni-directional pattern with good efficiency and cross-polarisation characteristics.
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