11,644 resources related to Spacecraft
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IEEE International Conference on Plasma Science (ICOPS) is an annual conference coordinated by the Plasma Science and Application Committee (PSAC) of the IEEE Nuclear & Plasma Sciences Society.
The conference program will consist of plenary lectures, symposia, workshops andinvitedsessions of the latest significant findings and developments in all the major fields ofbiomedical engineering.Submitted papers will be peer reviewed. Accepted high quality paperswill be presented in oral and postersessions, will appear in the Conference Proceedings and willbe indexed in PubMed/MEDLINE & IEEE Xplore
2019 IEEE 58th Conference on Decision and Control (CDC)
The CDC is recognized as the premier scientific and engineering conference dedicated to the advancement of the theory and practice of systems and control. The CDC annually brings together an international community of researchers and practitioners in the field of automatic control to discuss new research results, perspectives on future developments, and innovative applications relevant to decision making, systems and control, and related areas.The 58th CDC will feature contributed and invited papers, as well as workshops and may include tutorial sessions.The IEEE CDC is hosted by the IEEE Control Systems Society (CSS) in cooperation with the Society for Industrial and Applied Mathematics (SIAM), the Institute for Operations Research and the Management Sciences (INFORMS), the Japanese Society for Instrument and Control Engineers (SICE), and the European Union Control Association (EUCA).
APEC focuses on the practical and applied aspects of the power electronics business. The conference addresses issues of immediate and long term importance to practicing power electronics engineer.
International Geosicence and Remote Sensing Symposium (IGARSS) is the annual conference sponsored by the IEEE Geoscience and Remote Sensing Society (IEEE GRSS), which is also the flagship event of the society. The topics of IGARSS cover a wide variety of the research on the theory, techniques, and applications of remote sensing in geoscience, which includes: the fundamentals of the interactions electromagnetic waves with environment and target to be observed; the techniques and implementation of remote sensing for imaging and sounding; the analysis, processing and information technology of remote sensing data; the applications of remote sensing in different aspects of earth science; the missions and projects of earth observation satellites and airborne and ground based campaigns. The theme of IGARSS 2019 is “Enviroment and Disasters”, and some emphases will be given on related special topics.
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.
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 ...
Telephone, telegraphy, facsimile, and point-to-point television, by electromagnetic propagation, including radio; wire; aerial, underground, coaxial, and submarine cables; waveguides, communication satellites, and lasers; in marine, aeronautical, space and fixed station services; repeaters, radio relaying, signal storage, and regeneration; telecommunication error detection and correction; multiplexing and carrier techniques; communication switching systems; data communications; and communication theory. In addition to the above, ...
2018 2nd IEEE Advanced Information Management,Communicates,Electronic and Automation Control Conference (IMCEC), 2018
This paper describes an automatic generation method of spacecraft telemetry software code based on incremental model. First of all, a spacecraft incremental telemetry design model is established, including data system architecture model, detailed design model and system integration model. Secondly, the related parameter design of each telemetry design model is completed in turn. Then, each telemetry design model is automatically ...
2018 2nd IEEE Advanced Information Management,Communicates,Electronic and Automation Control Conference (IMCEC), 2018
In the spacecraft, 1553B bus controller is the central for the management of bus information exchange, whose reliability directly relates to system security. In recent years, due to the hash space environment in orbit, many cases of spacecraft bus RAM failures caused by the single event effect have occurred both at home and abroad. This paper presents a method for ...
2015 IEEE International Conference on Mechatronics and Automation (ICMA), 2015
The spacecraft which is composed by several modules should be tested on the ground whether the modules can be separated successfully or not, and separation locomotion data should be obtained as well. This paper has described the requirements and difficulties of separation test, and has designed the zero gravity platform. The critical design parameters are obtained by the analysis result ...
IEEE Transactions on Plasma Science, 2012
A series of spacecraft charging analyses was carried out for large GEO satellites using Multi-Utility Spacecraft Charging Analysis Tool. The purpose was to derive the number of electrostatic discharges expected for 15 years in orbit, which would be used as the basis of the number of primary electrostatic discharges (ESDs) to be used in future solar cell coupon ESD tests. ...
2017 5th International Conference on Mechanical, Automotive and Materials Engineering (CMAME), 2017
Spacecraft contains many flexible components and sampling parts, there are often many differences between real product and three-dimensional design models, so spacecraft component sometimes can't be installed due to component interference or small safety distance in assembly and integration process of spacecraft. Non-contact interference detection based on 3D scanner Handyscan 700 and Geomagic Control is designed, The Handyscan 700 which ...
Developing a Plasma Thruster in Costa Rica
Lunar Industrialization: The First Step to the Solar System
Engineering Our Future - Q and A with Panel
Superconducting Detectors for Astrophysics and Cosmology - ASC-2014 Plenary series - 9 of 13 - Thursday 2014/8/14
Power Electronics for the Space Exploration Hype: APEC 2019
Engineering The Future - Jon Spaihts Opening Remarks
This paper describes an automatic generation method of spacecraft telemetry software code based on incremental model. First of all, a spacecraft incremental telemetry design model is established, including data system architecture model, detailed design model and system integration model. Secondly, the related parameter design of each telemetry design model is completed in turn. Then, each telemetry design model is automatically transformed to software configuration code of onboard computer, which is compilable. Combination of the configuration code is used for the construction of the data pool based satellite telemetry software. Finally, the onboard software completes the telemetry data acquisition, storage, retrieval, grouping, scheduling, framing, virtual channel scheduling, the generation and transmission of telemetry frame by reading the corresponding configuration code.
In the spacecraft, 1553B bus controller is the central for the management of bus information exchange, whose reliability directly relates to system security. In recent years, due to the hash space environment in orbit, many cases of spacecraft bus RAM failures caused by the single event effect have occurred both at home and abroad. This paper presents a method for dealing with spacecraft in-orbit bus controller RAM failure. When such a fault occurs on the orbit of a spacecraft, the backup device is firstly enabled instead of the faulty device, and then the faulty device of the faulty device is located. A part of the software module of the bus controller RAM is reconstructed by sending a remote command from the ground to complete isolation of the chip fault area, and finally restore the main 1553B bus controller work to achieve the normal orbital operation of the spacecraft.
The spacecraft which is composed by several modules should be tested on the ground whether the modules can be separated successfully or not, and separation locomotion data should be obtained as well. This paper has described the requirements and difficulties of separation test, and has designed the zero gravity platform. The critical design parameters are obtained by the analysis result of MSC.ADAMS software. It can be concluded that the platform is correctly designed through verification of the prototype.
A series of spacecraft charging analyses was carried out for large GEO satellites using Multi-Utility Spacecraft Charging Analysis Tool. The purpose was to derive the number of electrostatic discharges expected for 15 years in orbit, which would be used as the basis of the number of primary electrostatic discharges (ESDs) to be used in future solar cell coupon ESD tests. The combinations of GEO plasma parameters (electron density, proton density, electron energy, and proton energy) that have a high probability of occurrence have been identified first. For each of those plasma parameters, a charging analysis was done. In the simulation, the time for the differential voltage between solar array cover glass and the spacecraft chassis to reach the ESD inception threshold was calculated. The results indicate that, for a typical GEO satellite, the expected number of ESDs in 15 years is on the order of 10 000, agreeing well with the previous work where another satellite was simulated by NASCAP/GEO.
Spacecraft contains many flexible components and sampling parts, there are often many differences between real product and three-dimensional design models, so spacecraft component sometimes can't be installed due to component interference or small safety distance in assembly and integration process of spacecraft. Non-contact interference detection based on 3D scanner Handyscan 700 and Geomagic Control is designed, The Handyscan 700 which is a portable scanner takes into account the measurement speed and accuracy. The experiment shows that this detection method can achieve flexible components interference analysis and quantitative measurement before the cabin board installation through virtual assembly.
Spacecraft charging (surface and internal) is complex physical phenomena that can have serious ramifications on mission success. The degree of spacecraft charging a spacecraft may experience is heavily dependent on both the surrounding space environment and spacecraft geometry (more specifically, the geometry and material makeup of the spacecraft). We will present a study focusing on the effects of using good design and materials to help mitigate risks due to spacecraft charging. We will review the important considerations and good design practices to ensure mission success.
Spacecraft charging in GEO particularly concerns dielectric surfaces that may charge to significant voltages relative to spacecraft ground because of the space environment. Testing materials helps to define the level of risk and to maintain confidence in a spacecraft's immunity to damaging effects. Another factor defining the risk involves numerical simulation of spacecraft charging. Several tools aim to calculate surface charging, which is particularly hazardous in harsh environments produced by geomagnetic sub storms, where particles in the energy range of a few to hundreds of kiloelectronvolts are present. The main codes include Nascap-2k, Spacecraft plasma Interaction Software (SPIS), MUSCAT, and Coulomb-2. They use different numerical and sometimes physical models and cross checking their results is a necessary process to achieve better confidence in simulations performed by spacecraft prime manufacturers. The objective of this paper is to simulate different GEO spacecraft configurations with NASA Charging Analyzer Program at geosynchronous orbits (a 1980s to 1990s predecessor to Nascap-2k) and SPIS and to compare the results, both in terms of absolute and differential potentials. The first section concerns the SCATHA spacecraft. The second part of this paper compares efforts to model a modern telecom spacecraft. Finally, we conclude on the reliability of the simulations performed and possible areas for modeling improvement.
The system health management technology uses observation data, system models, and relative intelligent algorithms to monitor system anomaly, evaluate system degradation, predict residual life, and further determine the corresponding maintenance and operation strategy. Recently, the in-orbit management work of spacecraft in China focuses on fault detection and diagnosis, whereas the spacecraft's health management technology stays in the framework study status. For the spacecraft's health monitoring, the theory and algorithm are important to support practical engineering. Therefore, this paper introduces the profust-reliability-based health monitoring method into the in-orbit management work of spacecraft. This method analyzes telemetry parameters of spacecraft, and calculates the profust reliability of telemetry parameters, component, and system, respectively. Then, the health level of the spacecraft is classified according to the calculated profust reliability value. This method provides a new thought to the in-orbit management work of spacecraft. The simulation result shows that this method can effectively evaluate the health status of spacecraft system.
Geosynchronous spacecraft charging has been a focus of attention since a large number of satellites are operating in this region. The most severe geosynchronous charging environment is during substorms, in which the plasma environment is generally better described by double Maxwellian distribution. In such case, determination of onset of spacecraft charging becomes more complex since more parameters are involved. In this paper, the threshold condition for onset of charging in double Maxwellian plasma is developed theoretically in a more general sense, and the charging behavior at the threshold is investigated in detail. It is found that sudden jump to negative potential of thousands of volts or more can take place at the threshold in certain situation. The mechanism underlying the potential jump is clarified from the stability theory and illustrated by typical calculations. Moreover, a more general condition for potential jump is determined theoretically, and consequently another threshold condition for jump in positive direction is found. At both thresholds, the spacecraft potentials are semisteady, but in opposite directions, with the possibility of a jump to a stable potential. The polarity of movement across the thresholds from different plasma will cause a spacecraft to experience irreversible charging histories which result in significant hysteresis.
The bistatic synthetic aperture radar (BiSAR) system consists of a geosynchronous Earth orbit (GEO) illuminator and a low Earth orbit (LEO) receiver. Compared with GEO SAR, it offers great advantages of higher signal- to-noise ratio (SNR) and finer spatial resolution with lower system complexity. The concept also raises significant technical challenges. The spacecraft formation has great effect on radar performance, such as spatial resolution, the angle of two-dimensional (2-D) resolution direction and noise- equivalent sigma zero (NESZ). This paper establishes the relationship between the imaging performance and the formation parameters. Then, a novel design method of spacecraft formation is presented, identifying the principal formation design choices and constraints. Finally, simulation results are provided for typical observational tasks, to verify the effectiveness of the proposed method.
Recommended practices for gyroscope and accelerometer testing are discussed, ranging from the equipment and instrumentation employed to the way that tests are carried out and data are acquired and analyzed.
Generate errata and/or revisions to the existing Std. 836-1991.
To review all of the definitions included in the standard and to revise them as required. New terminology will be added to bring the document up to date with current technology.
Telemetry Signals Analyst - Entry/Mid-Level
The National Security Agency
Space Systems Researcher - ACL
Georgia Tech Research Institute (GTRI)
Online Full-Time Faculty - Astronautical / Space Engineering - Assistant Prof
American Public University System