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Highly Elliptical Orbits for Polar Regions with Reduced Total Ionizing Dose

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Highly Elliptical Orbits for Polar Regions with Reduced Total Ionizing Dose Available online at www.sciencedirect.com ScienceDirect Advances in Space Research 63 (2019) 3761–3767 www.elsevier.com/locate/asr Highly elliptical orbits for polar regions with reduced total ionizing dose A.P. Trishchenko a,⇑, L.D. Trichtchenko b, L. Garand c a Canada Centre for Remote Sensing, Natural Resources Canada, Ottawa, ON, Canada b Space Weather Forecast Centre, Geological Survey of Canada, Natural Resources Canada, Ottawa, ON, Canada c Meteorological Research Division, Environment and Climate Change Canada, Dorval, QC, Canada Received 27 November 2018; received in revised form 16 March 2019; accepted 5 April 2019 Available online 13 April 2019 Abstract The 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. Crown Copyright Ó 2019 Published by Elsevier Ltd on behalf of COSPAR. This is an open access article under the CC BY-NC-ND license (http:// creativecommons.org/licenses/by-nc-nd/4.0/). Keywords: Space environment; Arctic; Highly elliptical orbit; Earth radiation belts; Total ionizing dose 1. Introduction 2019 (WMO, 2009, 2017). A number of studies has been conducted to determine the observing capacity of various The concept of Highly Elliptical Orbit (HEO) offers an HEO orbit configurations (Trishchenko and Garand, attractive opportunity to achieve continuous imaging of 2011; Trishchenko et al., 2011; Trishchenko et al. 2016), the Earth’s polar regions from space (Kidder and Vonder and the advantages of such a system relative to constella- Haar, 1990; Trishchenko et al., 2016). The World Meteoro- tion of satellites on the Low Earth Orbit (LEO) logical Organization (WMO) identified the need for such (Trishchenko and Garand, 2012) and the Medium Earth satellite observing system in its Vision 2025 document Orbit (MEO) constellations (Trishchenko et al., and the new Vision 2040 strategic plan to be adopted in submitted for publication). A HEO system named Atmo- spheric Imaging Mission for Northern Regions (AIM- North) has been recently proposed for air quality and green ⇑ Corresponding author. gas monitoring (Nassar et al., submitted for publication). E-mail addresses: [email protected] (A.P. Trishchen- The Three Apogee (TAP) 16-hr HEO orbit has been intro- ko), [email protected] (L.D. Trichtchenko), louis.garand@- duced to achieve the continuous Arctic imaging and to canada.ca (L. Garand). https://doi.org/10.1016/j.asr.2019.04.005 0273-1177/Crown Copyright Ó 2019 Published by Elsevier Ltd on behalf of COSPAR. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/). 3762 A.P. Trishchenko et al. / Advances in Space Research 63 (2019) 3761–3767 minimize the ionizing radiation dose from the trapped pro- therefore, is more suitable and beneficial for climate and tons (Trishchenko et al., 2011). The set of orbital elements weather observations from space. (Fig. 1) for the TAP orbit has been derived using an opti- A key consideration for designing the TAP orbit was a mization process based on four criteria: reduction of ionizing dose due to high-energy protons. This was achieved by devising the orbit that does not cross the (1) 100% continuous coverage of the polar region above area with large concentration of high-energy proton 60°N with the Viewing Zenith Angle (VZA) limit of (Trishchenko et al., 2011). This optimization scheme paid 70° (image refresh cycle of 10–15 min); less attention to minimizing the overall impact of electrons (2) the maximum altitude at the apogee point H a below and the total ionizing dose. In fact, not much else can be 45,000 km, i.e. not more than 25% higher than the achieved with this optimization approach, because the four geosynchronous (GEO) orbit; criteria listed above determine all major Keplerian orbital (3) the altitude of semilatus rectum of the orbit above the parameters shown in Fig. 1, i.e. the semi-major axis a, Earth’s surface greater than 15,000 km to avoid the the eccentricity e, the argument of perigee x, and the orbit region of trapped high-energy protons with energy inclination i. The remaining two Keplerian orbital ele- E>10MeV; ments, the right ascension of ascending node X and the true (4) the orbit inclination close to the critical value (mean) anomaly mðMÞ, determine the angular position of (63.435°) to ensure stable location of orbit defined the orbital plane in the celestial inertial coordinate system by the rotation of perigee. and the satellite position along the orbit (Duboshin, 1976). As such, they do not have significant impact on In comparison to 12-h Molniya HEO orbit widely the total radiation dose due to the cyclic nature of satellite employed for communication purposes and initially con- orbital motion. sidered for polar meteorological observations, the TAP This study focuses on minimizing the total radiation orbit reduces the radiation exposure to high-energy pro- dose for the 14-h, 15-h and 16-h HEO orbits, which is ben- tons by factor of 103–104. The projection of satellite ground eficial to extend the duration of the satellite mission. These track on the Earth’s surface for the 16-h TAP HEO orbit orbits are identified as the most practical for implementing has three stable positions of the apogee points. They are a continuous Arctic satellite observing system separated by 120° in longitude and can be conveniently (Trishchenko et al., 2016; Berquand, 2017). We conducted selected to observe areas over the North America, Europe this additional analysis by relaxing the criterion for a max- and Asia regions. imum altitude, i.e. allowing the apogee height H a to be lar- Trichtchenko et al. (2014) conducted a comprehensive ger than 45,000 km. This is equivalent to changing the obit analysis of the ionizing radiation environment for the fam- eccentricity (or perigee height). Based on conclusions from ily of HEO orbits with orbital periods ranging from 6 h to the analysis presented by Trichtchenko et al. (2014) for 24 h. The minimum of the total ionizing dose has been dis- orbits with periods longer than 14 h, the dominant ionizing covered for the range of orbital periods between 14 h and component are electrons of the outer radiation belt. Thus, 15 h. As a result of this analysis, a set of Multiple APogee the main idea is to see if the 14-h, 15-h and 16-h HEO (MAP) HEO orbits has been proposed (Trishchenko et al. orbits can fit better within the slot zone between the inner 2016). The MAP orbits with period of 14–15 h have drift- and outer electron belts to reduce the total ionizing dose ing (multiple) apogee locations with a repeat cycle of sev- (TID). eral days (7 and 5 days, correspondingly). This leads to more uniform distribution of observational geometry, reduces possible angular-dependent sampling biases and, 2. Orbital analysis The approach for the selection of orbital parameters is similar to that proposed by Trichtchenko et al. (2014). We consider the set of HEO orbits at critical inclination ÀÁpffiffiffi icr ¼ arccos 1= 5 63:435 , that ensures a minimal rotation of perigee (Duboshin, 1976; Vallado, 2007). Due to practical reasons, the limit of the perigee minimal alti- tude is set as H p 1000 km to avoid the area of near- Earth space densely populated by various man-made space objects (Gleghorn et al., 1995), to reduce atmospheric drag effects and to have some margins for natural orbit varia- tions and orbital maneuvers. The argument of perigee x should be equal to 270° to achieve location of the apogee at the highest latitude (equal to icr). The orbital period T Fig. 1. Graphical layout of elliptical orbit and definition of Keplerian is linked with a good accuracy to the semi-major axis a orbital elements. as follows A.P. Trishchenko et al. / Advances in Space Research 63 (2019) 3761–3767 3763 a1:5 3.
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