Req. ID | Statement |
---|---|
001 | The GENESIS mission shall be designed to achieve the main mission objective Obj-1, through the co-location in space of the following 4 geodetic techniques: GNSS, VLBI, SLR, DORIS |
002 | The GENESIS mission should be designed to achieve the main mission objective Obj-2, for operational time and frequency transfer and synchronization |
003 | The mission shall comply with the space debris mitigation regulations |
004 | The casualty risk for the mission shall not exceed 1 in 10000 for any re-entry event (controlled or uncontrolled). If the predicted casualty risk for an uncontrolled re-entry exceeds this value, an uncontrolled re-entry is not allowed and a targeted controlled re-entry shall be performed in order not to exceed a risk level of 1 in 10000 |
005 | The mission shall comply with the space debris mitigation requirements in the nominal and also in the failure case |
006 | The mission operational lifetime shall be at least 3 years, as a minimum, excluding LEOP, commissioning and disposal |
007 | The GENESIS mission should be designed for a development time of 3 to 4 years |
008 | The GENESIS mission should target a launch date in 2027 |
009 | Use of high-technical readiness level, demonstrated instruments and payloads shall be preferred, whenever possible |
010 | Maximum re-use of existing facilities at ESA and ESA Member States |
011 | The satellite should be launched into an orbit capable to fulfill the mission and payload requirements |
012 | A small satellite platform should be targeted |
013 | The satellite platform shall be able to accommodate all the GENESIS payloads associated to the geodetic techniques. Additionally, the platform should host the other enabling subsystems, as needed (and optional payloads as appropriate) |
014 | The platform nominal lifetime shall be at least 4 years |
015 | The offset between each payload and the satellite CoM shall be known with accuracy of 1 mm. Offset stability shall remain within 1 mm level during the whole duration of the mission |
016 | The CoM position should be known with 1 mm accuracy in the satellite reference frame |
017 | The satellite shall have a Nadir-pointing face for the whole mission duration, with a pointing accuracy less than 1 degree and a pointing stability of 0.1 degree along the whole orbit |
018 | The satellite platform shall be able to operate at the least 2 geodetic techniques in parallel at all times |
019 | Attitude determination shall be maintained at all times with accuracy below 0.1 degree |
020 | The POD will have to be able to determine the orbit with an accuracy better than 1 cm. POD is also affected by optical and thermal material properties (absorption, reflection and such) of the satellite outer surfaces to make an accurate radiation pressure model of the satellite. This has to be taken into account in CDF in particular with respect to impact on costs |
021 | The S/C shall be able to download a volume of science data as follows:Â GNSS tracking data (1Â Hz) 0.2Â GB/day; DORIS tracking data (0.1Â Hz) 0.04Â GB/day; Active SLR (SLR related, for synchronization between a ground clock linked to a laser station and a clock on board the satellite) 0.05Â GB/day; accelerometer 0.002Â GB/day |
022 | To provide the link with current ITRF realizations, the selected orbit shall be accessible by the established global tracking networks of the different techniques |
023 | VLBI shall be visible for 20 % time from at the least 2 VLBI stations separated by 10000Â km |
024 | The GENESIS Payloads are: GNSS receiver, VLBI transmitter, a DORIS Receiver and a SLR retro-reflector |
025 | A common time reference for all onboard instruments |
026 | An accelerometer for measuring the non-gravitational accelerations, contributing to POD should be included |