4 Final Report - Emits - ESA

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4 Final Report Direction MTG Scaled MTG Requirement Margin Lateral 19.32Hz 18.86Hz 17.25Hz 1.61Hz Longitudinal 40.65Hz 40.37Hz 40.25Hz 0.12Hz 4.5.8.2 Thermal Control Thermal Environment The Geo-Oculus spacecraft will circle the Earth in a geostationary orbit. It is positioned directly over the equator and follows it’s path in the equatorial plane at a speed matching the Earth’s rotation. Thus, the spacecraft completes one rotation around its North / South axis per day. The sun will traverse through an angle of ±23.5° perpendicular to the orbit plane during the year. The extremes will occur at the Winter Solstice and the Summer Solstice. Eclipses will occur during the Equinox seasons, with maximum eclipse duration of 72 minutes. The North face of the spacecraft will receive direct solar illumination for 6 months centred on the Summer Solstice, while the South face will receive direct solar illumination for 6 months centred on the Winter Solstice. The other faces of the spacecraft will receive varying solar illumination during each day. The Earth varies it’s distance from the Sun over a period of 1 year. This means that the solar constant at Earth’s location changes over the year from 1420 W/m 2 at Winter Solstice to 1327 W/m 2 at Summer Solstice. Thermal Control Concept The Geo-Oculus spacecraft body thermal control will rely primarily on passive means supported by electrical heaters. The North and South faces of the spacecraft are used as the main heat rejection paths. Externally they will be covered by Optical Solar Reflectors (OSR). The exact area of OSRs exposed to space will be regulated by the use of Multi-Layer Insulation (MLI). The inside of the panels will have a black finish. Aluminium doublers and heat pipes, as appropriate, will be used to spread the heat within the panel. All electronic units are mounted inside the spacecraft primary structure. Heat transfer from the dissipating units to the radiators relies mainly on conduction.. Thermal Performance The total dissipation of the equipments on the spacecraft is 1402 watts. 423 watts is the dissipation of the externally mounted units, leaving 979 watts dissipated within the spacecraft body. The payload electronics, 300 watts, is mounted on the North radiator. In addition, some of the bus equipment will also be mounted on the North panel such that the total amount of heat rejection capability adds up to 479 watts. The rest of the spacecraft bus electronics, 500 watts, is mounted on the South radiator. This allows the calculation of the radiator sizes and the required heater power. The analysis results are shown in Table 4.5-20 and Table 4.5-21. Page 4-76 Doc. No: GOC-ASG-RP-002 Issue: 2 Astrium GmbH Date: 13.05.2009
4 Final Report Table 4.5-20: Thermal Results for North Radiator North Radiator Dissipation 479 watts Margin 153 watts Total dissipated 632 watts Required radiator area 3.24 m 2 Heater power – Equinox sunlight 50 watts Heater power – Equinox eclipse 105 watts Table 4.5-21: Thermal Results for South Radiator South Radiator Dissipation 500 watts Margin 160 watts Total dissipated 660 watts Required radiator area 3.54 m 2 Heater power – Equinox sunlight 88 watts Heater power – Equinox eclipse 139 watts The North and South panel provide up to about 5 m 2 of radiator surface each which leaves sufficient margin for further evolution. 4.5.9 Satellite Budgets Geo-Oculus Budgets S/C Mass Power 4.6 Ground Segment Propulsion Dry Mass 1858 kg Launch Mass 3652 kg Power Demand 1800 W S/A Size (installed) 11 m 2 Communication Battery 135 Ah Tanks 4x406 ltr PDT 250 Mbit/sec 4.6.1 Ground Segment Architecture The architecture of the Ground Segment for the Geo-Oculus system takes into consideration the heritage of the Agency in operating EO satellites and within this context the consistency of the functionalities and of the implementation solutions with other EO systems operated by the Agency. In particular, the interoperability of Geo-Oculus with other EO systems serving the GMES needs is of paramount importance. Doc. No: GOC-ASG-RP-002 Page 4-77 Issue: 2 Date: 13.05.2009 Astrium GmbH
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Geo-Oculus: A Mission for Real-Time
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DL Final Distribution List Report Q
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4 Final Report - Emits - ESA

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