4 Final Report - Emits - ESA

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4 Final 4.5 Satellite Report 4.5.1 Configuration The basic features of the suggested baseline configuration as derived by the trade-offs documented in [RD 7] are as follows: • dual wing steerable solar array, • payload on top panel (launch) / Nadir panel (operation), • no yaw flip manoeuvre. The selected spacecraft configuration based on above inputs has been influenced by the choice of the favourable design of the chemical propulsion system as well as by the heritage available from similar projects. The resulting external configuration of the spacecraft in stowed condition is shown in Figure 4.5-1. The payload is connected to the platform via 3 bi-pods providing iso-static mounting conditions. The configuration of these bi-pods has still to be iterated and the provision of suitable hard-points in the platform, accordingly. The solar array wings are stowed on the side panels which correspond to the North and South panel during operational mode. The PDT antenna system comprises a deployable boom and is also folded to a side panel. The deployable boom is needed in order to provide visibility between antenna and ground station which is challenged by the big payload and, moreover, by the manoeuvres which point the complete spacecraft to the scene of interest. A similar problem concerns the S-Bd antenna which is roughly Nadir oriented (the complementary Zenith oriented antenna is hidden behind the spacecraft). Since this S-Bd antenna needs a hemispherical field of view, a mounting on the payload close to the entrance of the big baffle has been selected. This accommodation of platform equipment on the payload does not seem to be necessary for the infrared Earth sensors (IRES). Their field of view requirement is about 20 degree half cone angle and may be provided by putting these sensors on a pedestal. The situation is even a little more comfortable for the star trackers. They shall be aligned as close as possible with the payload line of sight direction in order to achieve the maximum attitude knowledge accuracy. However, they must also consider a certain Earth exclusion angle which yields an off-Nadir viewing direction. This together with the even narrower field of view (~15 degree half cone angle) allows to accommodate the star trackers directly on the top panel. This position may be revised in a later phase since the neighbouring payload radiator may evolve and the contribution of thermo-elastic deformations to the pointing knowledge budget may be optimised by mounting the star trackers directly on the payload. Page 4-48 Doc. No: GOC-ASG-RP-002 Issue: 2 Astrium GmbH Date: 13.05.2009
4 Final Report S-Bd Antenna Instrument X 3500 mm Y 2300 mm Z 2300 mm S/C Body X 2450 mm Y 2600 mm Z 2200 mm PDT Antenna Space Environment Sensor Figure 4.5-1: Stowed Configuration S-Bd Antenna Star Tracker IRES Sensors Figure 4.5-2 depicts the deployed configuration of the suggested baseline concept for Geo-Oculus. The upper solar array wing is oriented towards the North direction and the lower wing towards the South direction. The wings are steerable around the North – South axis thereby always providing an optimised sun inclination angle. The PDT antenna is also deployed to achieve a sufficient clearance between the antenna field of view and the payload. A 2-axis antenna pointing mechanism is installed directly under the antenna dish which is foreseen to compensate the manoeuvres for acquiring a new scene. Doc. No: GOC-ASG-RP-002 Page 4-49 Issue: 2 Date: 13.05.2009 Astrium GmbH LAE
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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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TOC Final Table of Content Report D
Page 13 and 14: 1 Final Report 1 Introduction 1.1 S
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Page 18 and 19: 2 Final Report capability of existi
Page 20 and 21: 2 Final Report Figure 2.3-1: Flood
Page 22 and 23: 2 Final Report Figure 2.3-3: Algal
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Page 107 and 108: A Final Report Annex A Abbreviation
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