|
Notice:
|
Found 208 entries in the Bibliography.
Showing entries from 201 through 208
| 2012 |
|
Injection and Acceleration of Charged Nano-Dust Particles from Sungrazing Comets It is proposed that the high-speed nanodust detected by the plasma wave instrument on the STEREO spacecraft could have an origin from the sungrazing comets. Trajectory calculations are performed using a simple analytical coronal magnetic field model to explore the dynamical nature of such charged nanodust in the vicinity of the solar corona. The relevance of this very near-solar source mechanism of nanodust and pickup ions to the Solar Probe Plus mission is also discussed. Published by: Published on: YEAR: 2012 DOI: 10.1063/1.4723586 |
|
Estimating Upper Limits of Solar Flare Hard X-Ray Fluences for Space Missions Near the Sun We present a method to estimate an upper limit of the mission integrated fluence of hard X-rays (HXRs) produced by solar flares for a probe traveling at heliocentric distances R<1 AU. By using (1) the number and peak of both soft X-ray (SXR) flares and microwave (MW) solar bursts observed during the last three solar cycles, (2) either frequency distributions of HXR flare parameters, or correlations between the HXR fluence and the SXR flare class or the MW burst flux intensity, and (3) virtual launches of the probe at differe ... Published by: Published on: YEAR: 2012 DOI: 10.1063/1.4768741 |
|
Use of Hydrocode Modeling to Develop Advanced MMOD Shielding Designs A multi-physics computations-based methodology for space debris hypervelocity impact (HVI) damage mitigation is presented. Specifically, improved debris mitigation through development of innovative, lightweight structural designs is described. The methodology has been applied to the design of the Solar Probe Plus (SPP) spacecraft to mitigate extreme solar microdust hypervelocity impacts (50-300 km/s) by the Johns Hopkins University Applied Physics Laboratory (JHU/APL). The methodology combines hydrocode computations of the c ... Iyer, Kaushik; Mehoke, Douglas; Brown, Robert; Swaminathan, P.; Carrasco, Cesar; Batra, Romesh; Published by: Published on: YEAR: 2012 DOI: 10.1109/AERO.2012.6187075 |
| 2011 |
|
Concentrated Solar Energy to Study High Temperature Materials for Space and Energy In this paper, the concentrated solar energy is used as a source of high temperatures to study the physical and chemical behaviors and intrinsic properties of refractory materials. The atmospheres surrounding the materials have to be simulated in experimental reactors to characterize the materials in real environments. Several application fields are concerned such as the aerospace and the energy fields: examples of results will be given for the heat shield of the Solar Probe Plus mission (NASA) for the SiC/SiC material that ... Charpentier, Ludovic; Dawi, Kamel; Eck, Julien; Pierrat, Baptiste; Sans, Jean-Louis; Balat-Pichelin, Marianne; Published by: JOURNAL OF SOLAR ENERGY ENGINEERING-TRANSACTIONS OF THE ASME Published on: AUG YEAR: 2011 DOI: 10.1115/1.4004241 |
|
A method to estimate both solar energetic particle mission-integrated fluences and solar energetic particle peak intensities for missions traveling through the innermost part of the heliosphere (r \< 1 AU) is presented. By using (1) an extensive data set of particle intensities measured at 1 AU over the last three solar cycles, (2) successive launch dates for the mission traveling close to the Sun over the time interval spanned by our data set, and (3) appropriate radial dependences to extrapolate fluences and peak int ... Published by: Space Weather Published on: 11/2011 YEAR: 2011 DOI: 10.1029/2011SW000708 Interplanetary Physics: Energetic particles (7514); Interplanetary Physics: Instruments and techniques; Interplanetary Physics: Solar cycle variations (7536); Parker Data Used; parker solar probe; Solar Probe Plus; space weather |
|
The aim of the Solar Probe Plus (SP+) mission is to understand how the solar corona is heated and how the solar wind is accelerated. To achieve these goals, in situ measurements are necessary and the spacecraft has to approach the Sun as close as 9.5 solar radii. This trajectory induces extreme environmental conditions such as high temperatures and intense Vacuum Ultraviolet radiation (VUV). To protect the measurement and communication instruments, a heat shield constituted of a carbon material is placed on the top of the ... Eck, J.; Sans, J.-L.; Balat-Pichelin, M.; Published by: Applied Surface Science Published on: 02/2011 YEAR: 2011 DOI: 10.1016/j.apsusc.2010.10.139 |
| 2010 |
|
Solar Probe Plus: Mission design challenges and trades NASA plans to launch the first mission to the Sun, named Solar Probe Plus, as early as 2015, after a comprehensive feasibility study that significantly changed the original Solar Probe mission concept. The original Solar Probe mission concept, based on a Jupiter gravity assist trajectory, was no longer feasible under the new guidelines given to the mission. A complete redesign of the mission was required, which called for developing alternative trajectories that excluded a flyby of Jupiter. Without the very powerful gravi ... Published by: Acta Astronautica Published on: 11/2010 YEAR: 2010 DOI: 10.1016/j.actaastro.2010.06.007 |
|
THE SOLAR PROBE PLUS SOLAR ARRAY DEVELOPMENT AND DESIGN The Solar Probe Plus (SPP) spacecraft will orbit as closely as 9.5 solar radii from the sun; so close that its thermal protection shield (TPS) will reach a peak temperature of 1,400C. To work in this environment, the solar array will use pressurized water cooling and operate in the penumbra formed by the TPS at a 68 degrees angle of incidence. Even with these mitigations, the array will be subject to extremely high intensity and temperature. This paper will summarize the array s environment, present a preliminary design, out ... Gaddy, Edward; Decker, Rob; Lockwood, Mary; Roufberg, Lew; Knutzen, Gayle; Marsh, Danielle; Published by: Published on: YEAR: 2010 DOI: 10.1109/PVSC.2010.5617077 |
