ExoMars Mission rd Industry Day. Torino October 9th, TASI -Torino October 09, DOC-TAS-EN-002
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1 DOC-TAS-EN-002 ExoMars Mission rd Industry Day Torino October 9th, 2013
2 3rd ExoMars Industry Day for 2018 Mission Mission and System
3 International cooperation 2018 Mission within ESA-ROS international cooperation 2018 Mission Trace Gas Orbiter (TGO) NASA DSN N/A Available for extreme contingencies during Cruise Spacecraft Composite (Carrier Module + Descent Module + Rover Module) Roscosmos RNS ESA ESTRACK DSN ROCC (incl SOC- Altec) ESOC, Darmstadt Spacecraft Operations Archiving (ESAC) Archiving (ROS) Lander Op. Center (ROS) Rover and Landing Platform Proton M / Breeze M
4 EXOMARS 2018 Reference Missions Nominal Mission 2018 Short Transfer Launch date: 07 May 2018 Mars Arrival: 15 January 2019 Transfer duration: days Arrival LS: 324 With arrival velocity range [ km/s] PROGRADE entry: Relative velocity range [ km/s] Reference Back-Up Mission 2020 Short Transfer with late arrival Launch date: 05 August 2020 Mars Arrival: 19 April 2021 Transfer duration: days Arrival LS: 34 With arrival velocity range [ km/s] PROGRADE entry: Relative velocity is [ km/s]
5 EXOMARS 2018 Reference Mission Main Requirements Communication Requirements Spacecraft Composite housekeeping data return of 200 Mb/day (To be Confirmed) during all mission phases Spacecraft Composite During all mission phases, the Spacecraft Composite shall support reception of commands from Ground Control at a minimum data rate of 2000 bps. Mission to be designed to allow visibility from Earth of the EDL event Essential telemetry transmitted at 8 kbps by the DM during the Coast and EDL phases to allow real time transmission to, and reception by, the 2016 TGO. The relay link shall be compatible with a Mars surface-to-orbiter data relay provided by the TGO (nominal mission) and any other available Mars Orbiters (NASA Relay Orbiter(s) as contingency case Average data relay return of 0.4 Gb/day for the two surface assets
6 EXOMARS 2018 Reference Mission Main Requirements Mass Requirements 2800 Kg at Launcher separation, including all maturity and system margins (w/o Launcher Adapter) Note: DMC Mass bounded to 2000 Kg NTE (including a 350 Kg class Rover Module Power Requirements 1200 W (400 W to DMC during Cruise) implies foldable Solar Panels on CM Single Failure Tolerance (not applicable to RDA and to RCT Configuration for Torque/Force Free Control) GNC Spinning Spacecraft during Cruise and DM ballistic EDL Operational LifeTime SCC/CM: 1 year DM-SP: 2 years RM: 0.6 year
7 System Design Status: SCC Avionics Descent Module Composite (DMC) CARRIER MODULE (CM) BACK SHELL (BSH) FRON SHIELD (FS) STR-1 STR-2 BATT SA PDD TCS heaters AC 1 Entry Sensors AC 1 Thermistors SEP MECH SEP CONNECTOR AC 1 Entry Sensors LANDER PLATFORM (LP) SEP CONNECTOR SEP MECH CSS-1 IMU-1 CSS-2 CPCDU IMU-2 RDA RME-2 BRSA RDA Antennas UHF-1 SWITCH Propulsion 8 x 30N ctrl THR RCS sensors Pyro valves CRTU SEP CONNECTOR UHF-2 THRs ESA-OBC Pyro valves RCS TCS X- DST X- DST RCS sensors TWTA TWTA RFDN ROS-OBC PAYLOADs LGA3 LGA2 LGA1 HGA SEP MECH LPCDU LRTU ROVER MODULE PWR Sys. Data Handl. Sys. Thermal Contr. Sys. Telecom. Sys. GNC. Sensors Actuators Propulsion Sys KEY Separ. Interfaces Discrete lines MIL-1553 bus RS-422/485 PWR/Pyro lines CAN bus Sensors BATT SA TCS heaters Legs AC 1 release Legs AC 1 Thermistors Legs AC 1 sensors Ramps AC 1 release Ramps AC 1 sensors Ramps Ramps AC 1 actuators SEP CONNECTOR RV HDRM RM-OBC PCDE ADE
8 System Design Status: SCC Configuration
9 System Design Status: CM Configuration Thruster 2x4 Star Tracker CRTU Tank Battery Central Tube mm I/F to separation mechanism of DM Battery Star Tracker Thruster 2x4 Solar Generator Tank Radiator PCDU Deployable Solar panel LGA TWT Transceiver EPC 1666mm Launcher I/F MGA
10 System Design Status: DMC Configuration Preliminary CAD model of the Descent Module delivered by LAV.
11 System Design Status: DMC Configuration
12 System Design Status: DMC Configuration
13 Rover Module Configuration ISEM Optical Head PanCam Navigation cameras Pan and Tilt Mechanism Deployable Mast Assembly Loc cameras UHF Antenna ALD Radiators Core Sample transportation mechanism port Deployable solar panels Drill Box DBE/MaMiss Elec Clupi Actuator Drive Electronic SVM Radiator Bogey Electromechanical assembly
14 TASI CM Upcoming procured items EXOMARS Mission 2018 Spacecraft Composite EXOMARS Mission 2018 Carrier Module EXOMARS Mission 2018 Descent Module EXOMARS Mission 2018 Rover Module
15 Star Tracker Item: Autonomous Star Tracker Procuring Company: TAS-I ITT issue: Q K/O: Q Date of Need (PFM): Q Short description: Autonomous Star Tracker unit to provide attitude quaternion for spin stabilized spacecraft. The unit shall include dedicated baffle to be protected from any stray-light solar, lunar, Earth, Mars, planetary or other sources in the FoV Main requirements: Accuracy: 0.05 deg 3-sigma; Compatible with spin rate range between 2.5 to 3 5 rpm, with bore-sight radially mounted wrt spin axis Average power consumption 13W, data I/F preferred MIL-STD-1553 bus Star Catalog set-up to cover all interplanetary mission Models: STM, E(Q)M, 2xFM, FM Spare (tbc) Main Reviews: PDR, CDR, QR, DRB. Notes: In case of an OTS unit the reviews shall be limited according to unit qualification status
16 Cruise GNC algorithms Item: Cruise GNC algorithm design & verification support Procuring Company: TAS-I ITT issue: Q K/O: Q Date of Need: Q Short description: Task I: analytical verification of Guidance Navigation and Control algorithms for Cruise phase in support to detailed design phase Task II: evaluation of results and algorithm optimization during GNC verification activities on ATB Main requirements: GNC for attitude orientation control of Spin spacecraft (2.5rpm) with pointing accuracy 1deg half-cone during cruise, 0.2deg half cone at pre-separation GNC for trajectory control with autonomous delta-v determination 1% and implementation GNC architecture: IMU, STR, Sun Sensor. Delta-DOR (TBC) Models: Technical notes, Verification report, contribution to system documentation Main Reviews: input to system CDR Notes:
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