@article{Staat2012,
  author    = {Staat, Manfred},
  title     = {Limit and shakedown analysis under uncertainty},
  series = {Tap chi Khoa hoc \& ung dung - Dai hoc Ton Duc Thang},
  volume    = {19},
  journal   = {Tap chi Khoa hoc \& ung dung - Dai hoc Ton Duc Thang},
  pages     = {45 -- 47},
  year      = {2012},
  language  = {en}
}
@article{MansurovDigelBiisenbaevetal.2012,
  author    = {Mansurov, Z. and Digel, Ilya and Biisenbaev, M. and Savistkaya, I. and Kistaubaeva, A. and Akimbekov, N. and Zhubanova, A.},
  title     = {Bio-composite material on the basis of carbonized rice husk in biomedicine and environmental applications},
  series = {Eurasian Chemico-Technological Journal},
  volume    = {14},
  journal   = {Eurasian Chemico-Technological Journal},
  number    = {2},
  publisher = {Institute of Combustion Problems},
  address   = {Almaty},
  issn      = {2522-4867},
  doi       = {10.18321/ectj105},
  pages     = {115 -- 131},
  year      = {2012},
  language  = {en}
}
@article{LoebSchartnerDachwaldetal.2012,
  author    = {Loeb, Horst Wolfgang and Schartner, Karl-Heinz and Dachwald, Bernd and Ohndorf, Andreas and Seboldt, Wolfgang},
  title     = {Interstellar heliopause probe},
  series = {Труды МАИ},
  journal   = {Труды МАИ},
  number    = {60},
  publisher = {Moskauer Staatliches Luftfahrtinstitut (МАИ)},
  address   = {Moskau},
  pages     = {2 -- 2},
  year      = {2012},
  abstract  = {There is common agreement within the scientific community that in order to understand our local galactic environment it will be necessary to send a spacecraft into the region beyond the solar wind termination shock. Considering distances of 200 AU for a new mission, one needs a spacecraft traveling at a speed of close to 10 AU/yr in order to keep the mission duration in the range of less than 25 yrs, a transfer time postulated by European Space Agency (ESA). Two propulsion options for the mission have been proposed and discussed so far: the solar sail propulsion and the ballistic/radioisotope-electric propulsion (REP). As a further alternative, we here investigate a combination of solar-electric propulsion (SEP) and REP. The SEP stage consists of six 22-cms diameter RIT-22 ion thrusters working with a high specific impulse of 7377 s corresponding to a positive grid voltage of 5 kV. Solar power of 53 kW at begin of mission (BOM) is provided by a lightweight solar array.},
  language  = {en}
}