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TitleHighly elliptical orbits for polar regions with reduced total ionizing dose
AuthorTrishchenko, A P; Trichtchenko, L D; Garand, L
SourceAdvances in Space Research vol. 63, issue 12, 2019 p. 3761-3767, https://doi.org/10.1016/j.asr.2019.04.005 (Open Access)
Year2019
Alt SeriesNatural Resources Canada, Contribution Series 20190017
PublisherElsevier BV
Documentserial
Lang.English
Mediapaper; on-line; digital
File formatpdf (Adobe® Reader®); html
Subjectsgeophysics; remote sensing; satellites; modelling; models; satellite orbits; Multiple Apogee Highly Elliptical Orbit; apogee altitude limit; radiation; total ionizing dose; shielding thickness; mission lifetime
Illustrationsschematic representations; graphs; tables
ProgramMethodology, Remote Sensing Science
Released2019 04 13
AbstractThe study reports results of analysis related to minimization of the total ionizing dose (TID) for the Multiple Apogee Highly Elliptical Orbit with periods 14 h, 15 h and 16 h introduced earlier for continuous observation of the Earth's polar regions. The modeling of space environment has been conducted with use of the European Space Agency's SPENVIS tool based on the AE8/AP8 radiation models. Originally, the set of orbital parameters has been derived through the optimization process that included among other factors criteria for the apogee height limit and minimization of the radiation dose caused by trapped protons. By relaxing the apogee altitude limit, this study found the total ionizing dose TID can be significantly reduced for 15-h and 16-h orbits, while the originally proposed 14-h orbit is already at the minimum of radiation dose. For 15-h and 16-h orbits this converts into reduction of the thickness of aluminum shielding by factor 1.24-1.28 or an equivalent increase in the mission lifetime by up to 8.1 years. For example, an increase in apogee altitude to 49,620 km for 16-h orbit (eccentricity e = 0.74) in comparison to the originally proposed 16-h orbit (altitude equal to 43,500 km, e = 0.55) reduces the TID so that the shielding thickness decreases to 3.53 mm, instead of 4.35 mm of aluminum slab for the same 15-year duration of mission. Decrease of the TID is achieved due to significant reduction of ionizing radiation from the trapped electrons through the better placing of the orbit trajectory in the slot area, but at the expense of slight increase of ionizing radiation from the trapped protons and increase in apogee altitude to 46,640 km and 49,620 km for 15-h and 16-h orbit, correspondingly.
Summary(Plain Language Summary, not published)
The study reports results related to minimization of the total ionizing doze (TID) for the Highly Elliptical Orbit with periods 14 h, 15 h and 16 h introduced earlier for continuous Arctic observations. Originally, the set of orbital parameters has been derived through the optimization that included criteria for the apogee height limit and minimization of the proton radiation doze. By relaxing the apogee altitude limit, this study found the total ionizing doze TID can be significantly reduced for 15-h and 16-h orbits, while the originally proposed 14-h orbit is already at the minimum of radiation doze. For 15-h and 16-h orbits this converts into reduction of the thickness of aluminum shielding by factor 1.24-1.28 or an equivalent increase in the mission lifetime. Decrease of the TID is achieved due to reduction of ionizing radiation from the electrons through the better placing of the orbit in the slot area between inner and outer electron radiation belts.
GEOSCAN ID314612