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961.
T.G. Guzik J.H. Adams Jr. H.S. Ahn G.L. Bashindzhagyan K.E. Batkov J. Chang M. Christl A.R. Fazely O. Ganel R.M. Gunashingha J. Isbert K.C. Kim E.N. Kouznetsov M.I. Panasyuk A.D. Panov W.K.H. Schmidt E.S. Seo N.V. Sokolskaya J.W. Watts J.P. Wefel J. Wu V.I. Zatsepin 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2008
The Advanced Thin Ionization Calorimeter (ATIC) experiment is designed to investigate the charge composition and energy spectra of primary cosmic rays over the energy range from about 1011 to 1014 eV during Long Duration Balloon (LDB) flights from McMurdo, Antarctica. Currently, analysis from the ATIC-1 test flight and ATIC-2 science flight is underway and preparation for a second science flight is in progress. Charge identification of the incident cosmic ray is accomplished, primarily, by a pixilated Silicon Matrix detector located at the very top of the instrument. While it has been shown that the Silicon Matrix detector provides good charge identification even in the presence of electromagnetic shower backscatter from the calorimeter, the detector only measures the charge once. In this paper, we examine use of the top scintillator hodoscope detector to provide a second measure of the cosmic ray charge and, thus, improve the ATIC charge identification. 相似文献
962.
E.S. Seo H.S. Ahn P. Allison M.G. Bagliesi L. Barbier A. Barrau R. Bazer-Bachi J.J. Beatty G. Bigongiari P. Boyle T.J. Brandt M. Buénerd J.T. Childers N.B. Conklin S. Coutu L. Derome M.A. DuVernois O. Ganel J.H. Han J.A. Jeon K.C. Kim M.H. Lee L. Lutz A. Malinin M. Mangin-Brinet P.S. Marrocchesi P. Maestro A. Menchaca-Rocha S. Minnick S.I. Mognet S. Nam S. Nutter I.H. Park N.H. Park A. Putze R. Sina S. Swordy S. Wakely P. Walpole J. Wu J. Yang Y.S. Yoon R. Zei S.Y. Zinn 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2008
The Cosmic-Ray Energetics And Mass balloon-borne experiment has been launched twice in Antarctica, first in December 2004 and again in December 2005. It circumnavigated the South Pole three times during the first flight, which set a flight duration record of 42 days. A cumulative duration of 70 days within 13 months was achieved when the second flight completed 28 days during two circumnavigations of the Pole on 13 January 2006. Both the science instrument and support systems functioned extremely well, and a total 117 GB of data including 67 million science events were collected during these two flights. Preliminary analysis indicates that the data extend well above 100 TeV and follow reasonable power laws. The payload recovered from the first flight has been refurbished for the third flight in 2007, whereas the payload from the second flight is being refurbished to be ready for the fourth flight in 2008. Each flight will extend the reach of precise cosmic-ray composition measurements to energies not previously possible. 相似文献
963.
T. Ma J. Chang N. Zhang M.S. Cai Y.Z. Gong H.S. Tang R.J. Zhang N.S. Wang M. Yu J.P. Mao S.B. Su Z. Fang R. Xu Y.M. Hu Q. Gu Y.L. Zhou A.A. Xu L.G. Liu 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2008
Gamma-ray spectrometer (GRS) is included in the payload of Chinese first lunar mission Chang’E-1 that will be launched in 2007. Specific objectives of the GRS are to map abundance of O, Si, Fe, Ti, U, Th, K, and perhaps, Mg, Al, and Ca to depths of about 20 cm. There are remarkable advantages for GRS application to remote sensing elemental materials over the entire lunar surface: large effective area and good ability for background rejection. We will describe the design of GRS and present its performance in this paper. Moreover, the GRS calibration will also be introduced. 相似文献
964.
A conceptual configuration of the lunar base bioregenerative life support system including soil-like substrate for growing plants 总被引:1,自引:0,他引:1
H. Liu C.Y. Yu N.S. Manukovsky V.S. Kovalev Yu L. Gurevich J. Wang 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2008
The paper presents a conceptual configuration of the lunar base bioregenerative life support system (LBLSS), including soil-like substrate (SLS) for growing plants. SLS makes it possible to combine the processes of plant growth and the utilization of plant waste. Plants are to be grown on SLS on the basis of 20 kg of dry SLS mass or 100 kg of wet SLS mass per square meter. The substrate is to be delivered to the base ready-made as part of the plant growth subsystem. Food for the crew was provided by prestored stock 24% and by plant growing system 76%. Total dry weight of the food is 631 g per day (2800 kcal/day) for one crew member (CM). The list of candidate plants to be grown under lunar BLSS conditions included 14 species: wheat, rice, soybean, peanuts, sweet pepper, carrots, tomatoes, coriander, cole, lettuce, radish, squash, onion and garlic. From the prestored stock the crew consumed canned fish, iodinated salt, sugar, beef sauce and seafood sauce. Our calculations show that to provide one CM with plant food requires the area of 47.5 m2. The balance of substance is achieved by the removal dehydrated urine 59 g, feces 31 g, food waste 50 g, SLS 134 g, and also waters 86 g from system and introduction food 236 g, liquid potassium soap 4 g and mineral salts 120 g into system daily. To reduce system setup time the first plants could be sowed and germinated to a certain age on the Earth. 相似文献
965.
N. Gopalswamy A. Lara P.K. Manoharan R.A. Howard 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2005,36(12):2289-2294
We extend the empirical coronal mass ejection (CME) arrival model of Gopalswamy et al. [Gopalswamy, N. et al. Predicting the 1-AU arrival times of coronal mass ejections, J. Geophys. Res. 106, 29207, 2001] to predict the 1-AU arrival of interplanetary (IP) shocks. A set of 29 IP shocks and the associated magnetic clouds observed by the Wind spacecraft are used for this study. The primary input to this empirical shock arrival model is the initial speed of white-light CMEs obtained using coronagraphs. We use the gas dynamic piston–shock relationship to derive the ESA model which provides a simple means of obtaining the 1-AU speed and arrival times of interplanetary shocks using CME speeds. 相似文献
966.
S. Kodaira R.V. Tolochek I. Ambrozova H. Kawashima N. Yasuda M. Kurano H. Kitamura Y. Uchihori I. Kobayashi H. Hakamada A. Suzuki I.S. Kartsev E.N. Yarmanova I.V. Nikolaev V.A. Shurshakov 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
The dose reduction effects for space radiation by installation of water shielding material (“protective curtain”) of a stack board consisting of the hygienic wipes and towels have been experimentally evaluated in the International Space Station by using passive dosimeters. The averaged water thickness of the protective curtain was 6.3 g/cm2. The passive dosimeters consisted of a combination of thermoluminescent detectors (TLDs) and plastic nuclear track detectors (PNTDs). Totally 12 passive dosimeter packages were installed in the Russian Service Module during late 2010. Half of the packages were located at the protective curtain surface and the other half were at the crew cabin wall behind or aside the protective curtain. The mean absorbed dose and dose equivalent rates are measured to be 327 μGy/day and 821 μSv/day for the unprotected packages and 224 μGy/day and 575 μSv/day for the protected packages, respectively. The observed dose reduction rate with protective curtain was found to be 37 ± 7% in dose equivalent, which was consistent with the calculation in the spherical water phantom by PHITS. The contributions due to low and high LET particles were found to be comparable in observed dose reduction rate. The protective curtain would be effective shielding material for not only trapped particles (several 10 MeV) but also for low energy galactic cosmic rays (several 100 MeV/n). The properly utilized protective curtain will effectively reduce the radiation dose for crew living in space station and prolong long-term mission in the future. 相似文献
967.
J. Isbert J.H. Adams Jr. H.S. Ahn G.L. Bashindzhagyan K.E. Batkov M. Christl A.R. Fazely O. Ganel R.M. Gunashingha T.G. Guzik J. Chang K.C. Kim E.N. Kouznetsov Z.W. Lin M.I. Panasyuk A.D. Panov W.K.H. Schmidt E.S. Seo N.V. Sokolskaya John W. Watts J.P. Wefel J. Wu V.I. Zatsepin 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2008
The Advanced Thin Ionization Calorimeter (ATIC) Balloon Experiment had a successful test flight and a science flight in 2000–01 and 2002–03 and an unsuccessful launch in 2005–06 from McMurdo, Antarctica, returning 16 and 19 days of flight data. ATIC is designed to measure the spectra of cosmic rays (protons to iron). The instrument is composed of a Silicon matrix detector followed by a carbon target interleaved with scintillator tracking layers and a segmented BGO calorimeter composed of 320 individual crystals totaling 18 radiation lengths to determine the particle energy. BGO (Bismuth Germanate) is an inorganic scintillation crystal and its light output depends not only on the energy deposited by particles but also on the temperature of the crystal. The temperature of balloon instruments during flight is not constant due to sun angle variations as well as differences in albedo from the ground. The change in output for a given energy deposit in the crystals in response to temperature variations was determined. 相似文献
968.
N.J. Szewczyk J. Tillman C.A. Conley L. Granger L. Segalat A. Higashitani S. Honda Y. Honda H. Kagawa R. Adachi A. Higashibata N. Fujimoto K. Kuriyama N. Ishioka K. Fukui D. Baillie A. Rose G. Gasset B. Eche D. Chaput M. Viso 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2008
969.
Y. Saito D. Akita H. Fuke I. Iijima N. Izutsu Y. Kato J. Kawada Y. Matsuzaka E. Mizuta M. Namiki N. Nonaka S. Ohta T. Sato M. Seo A. Takada K. Tamura M. Toriumi T. Yamagami K. Yamada T. Yoshida K. Matsushima S. Tanaka 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2012
Development of a balloon to fly at higher altitudes is one of the most attractive challenges for scientific balloon technologies. After reaching the highest balloon altitude of 53.0 km using the 3.4 μm film in 2002, a thinner balloon film with a thickness of 2.8 μm was developed. A 5000 m3 balloon made with this film was launched successfully in 2004. However, three 60,000 m3 balloons with the same film launched in 2005, 2006, and 2007, failed during ascent. The mechanical properties of the 2.8 μm film were investigated intensively to look for degradation of the ultimate strength and its elongation as compared to the other thicker balloon films. The requirement of the balloon film was also studied using an empirical and a physical model assuming an axis-symmetrical balloon shape and the static pressure. It was found that the film was strong enough. A stress due to the dynamic pressure by the wind shear is considered as the possible reason for the unsuccessful flights. A 80,000 m3 balloon with cap films covering 9 m from the balloon top will be launch in 2011 to test the appropriateness of this reinforcement. 相似文献
970.
T. Joseph W. Lazio R.J. MacDowall Jack O. Burns D.L. Jones K.W. Weiler L. Demaio A. Cohen N. Paravastu Dalal E. Polisensky K. Stewart S. Bale N. Gopalswamy M. Kaiser J. Kasper 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
The Radio Observatory on the Lunar Surface for Solar studies (ROLSS) is a concept for a near-side low radio frequency imaging interferometric array designed to study particle acceleration at the Sun and in the inner heliosphere. The prime science mission is to image the radio emission generated by Type II and III solar radio burst processes with the aim of determining the sites at and mechanisms by which the radiating particles are accelerated. Specific questions to be addressed include the following: (1) Isolating the sites of electron acceleration responsible for Type II and III solar radio bursts during coronal mass ejections (CMEs); and (2) Determining if and the mechanism(s) by which multiple, successive CMEs produce unusually efficient particle acceleration and intense radio emission. Secondary science goals include constraining the density of the lunar ionosphere by searching for a low radio frequency cutoff to solar radio emission and constraining the low energy electron population in astrophysical sources. Key design requirements on ROLSS include the operational frequency and angular resolution. The electron densities in the solar corona and inner heliosphere are such that the relevant emission occurs at frequencies below 10 MHz. Second, resolving the potential sites of particle acceleration requires an instrument with an angular resolution of at least 2°, equivalent to a linear array size of approximately 1000 m. Operations would consist of data acquisition during the lunar day, with regular data downlinks. No operations would occur during lunar night. 相似文献