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83230913-DOC-TAS-EN-002 ExoMars-2018 DM Entry Decent Landing LSSWS#2 11-12 December 2014 Turin.

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Presentation on theme: "83230913-DOC-TAS-EN-002 ExoMars-2018 DM Entry Decent Landing LSSWS#2 11-12 December 2014 Turin."— Presentation transcript:

1 DOC-TAS-EN-002 ExoMars-2018 DM Entry Decent Landing LSSWS# December 2014 Turin

2 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space DM Entry Descent & Landing Summary DM Entry Descent and Landing System (EDLS) DM Entry Descent and Landing phase Approach to design Entry Corridors Entry corridor constraints Entry corridor analysis results & landing ellipse azimuth Oxia Planum Aram Dorsum Mawrth Vallis Hypanis Vallis Conclusions LSSWS#2 Torino Dec

3 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space DM Entry Descent and Landing System (EDLS) LSSWS#2 Torino Dec EDLS is composed by: Aeroshell (Front shield and Rear jacket) Parachute system Reaction Control Sub-system Main Braking Engine Attitude Thrusters Landing Legs Navigation Sub-system RDA IMU Aeroshell Main Braking Engine Attitude Thrusters Landing Legs

4 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space EDLS : Aeroshell “MER-like” Aeroshell 70° front shield 37° rear jacket External diameter 3.8 m Thermal protection system Based on silicon rubber and hollow glass microspheres Designed to withstand to 750 kW/m 2 stagnation 50 MJ/m 2 LSSWS#2 Torino Dec

5 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space PAS Objectives Reduce DM velocity down to 50 m/s Provide a safe distancing of FS and DM after separation Design: 2 mortars 2 pilot chute (DGB/EXM2016 Huygens derived) 1 15m-supersonic parachute (DGB/EXM2016 Huygens derived) 1 35m-subsonic parachute (RingSlot) EDLS : Parachute System LSSWS#2 Torino Dec

6 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space EDLS : Reaction Control Sub-system LSSWS#2 Torino Dec Fuel Tanks (Hydrazine) Platform Attitude Thrusters Pressurizing Gas Soft Landing Braking Engine

7 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space EDLS : Landing Legs Deployment soon after FS separation Landing clearance after landing legs deformation compatible with 350 mm rock height. LSSWS#2 Torino Dec

8 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space EDLS : Navigation Sub-Sytem IMU is used for the whole EDL phase RDA is used for the terrain relative navigation LSSWS#2 Torino Dec RDA Fuel Tank IMU#1 RDA Pressurizer IMU#2 Braking Engine Attitude Thrusters Landing Legs

9 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space DM Entry Descent and Landing phase scheme LSSWS#2 Torino Dec

10 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Approach to design Entry Corridors 1/2 Entry corridor entry trajectory angle domain that allow a safe landing LSSWS#2 Torino Dec The boundaries of this region are the steep and shallow trajectories that cannot be exceeded otherwise the entry cannot be performed safely or meeting the mission requirements Driven by the DM EDLS design characteristics and mission requirements Drag too low Deceleration too high Entry Corridor Shallow trajectory Steep trajectory

11 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Approach to design Entry Corridors 2/2 Entry corridor methods is Monte Carlo based For DM mass value of 2000kg at EIP, for each landing site and for each target IFPA (-11°, -11.5°, -12°, -12.5°, -13°) 1000 shots of possible trajectories for each atmospheric scenario (COLD, DUST and WARM) of MCD 5.0 were performed. (GCM winds perturbation was included) Dispersed entry conditions (Position and Velocity) were considered for LPO mission scenario The same vehicle configuration and EDL scheme was considered Dispersion of DM and Parachutes aerodynamic characteristics was considered Same EDL scheme (commands) was considered 1 st parachute deployment trigger, within a mach window, is g-load based 2 nd parachute deployment trigger, below mach 0.8, is time triggered (~18s) Front shield is released 7sec after the 2 nd parachute command issuing LSSWS#2 Torino Dec

12 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Entry corridor constraints1/3 Mechanical g-load: maximum load factor that the DM can withstand Heat Flux: it refers to the thermal protection system technology (material, process, qualification tests) Heat load: it refers to the thermal sizing (thickness) of Thermal Protection system Parachute inflation force: related to the type of parachute and its structural design : The trajectory shall be such to avoid over load on parachute that could damage it ! Mach range for parachute deployment detection accuracy: related to the performances of g-load activation algorithm and parachute qualification Landing accuracy: mission requirement Verticalization: related to the use of radar for relative navigation LSSWS#2 Torino Dec

13 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Entry corridor constraints2/3 From Monte Carlo shot for each target FPA the limit values are extracted and compared with the constraints to verify the available margin LSSWS#2 Torino Dec Margin 1 Positive margins Negative margins Heat load Mechanical g-load Landing accuracy Heat load Steep target FPA Shallow target FPA Flight Path Angle

14 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Applicable value for ExoMars-2018 Descent Module LSSWS#2 Torino Dec Entry corridor constraints3/3 PARAMETERVALUENOTES Thermal heat flux< 750 kW/m2 Thermal heat load< 50 MJ/m2 Load factor< 10 gWhole Trajectory 1st stage deployment MachMach < 2.2 GAT shall met the required performance (mach ) DGB (1st stage) Inflation force< 146kN 2nd stage deployment Mach Mach < 0.8 Ring Slot (2nd stage) Inflation force< 132kN Vericalization (FPA) angle at 1.5 km above ground < -75º Landing accuracy (semi-major axis)<50 km Size of dispersion ellipse at landing is 100 х 15 km

15 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Entry corridor analysis results Entry corridor analysis was executed on the LSSWG candidates landing regions Oxia Planum Aram Dorsum Mawrth Vallis Hypanis Vallis Variation of azimuth of landing ellipse was evaluated at the variation of target IFPA LSSWS#2 Torino Dec

16 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Entry corridor analysis results: Oxia Planum LSSWS#2 Torino Dec

17 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Landing Ellipse Azimuth : Oxia Planum 16 IFPA: ° IFPA: ° IFPA: ° IFPA: ° IFPA: ° Inertial Flight Path Angle [deg] Landing Ellipse Azimuth [deg]

18 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Entry corridor analysis results: Aram Dorsum LSSWS#2 Torino Dec

19 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Landing Ellipse Azimuth : Aram Dorsum 18 IFPA: ° IFPA: ° IFPA: ° IFPA: ° IFPA: ° Inertial Flight Path Angle [deg] Landing Ellipse Azimuth [deg]

20 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Entry corridor analysis results: Mawrth Vallis LSSWS#2 Torino Dec

21 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Landing Ellipse Azimuth : Mawrth Vallis 20 IFPA: ° IFPA: ° IFPA: ° IFPA: ° IFPA: ° Inertial Flight Path Angle [deg] Landing Ellipse Azimuth [deg]

22 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Entry corridor analysis results : Hypanis Vallis LSSWS#2 Torino Dec

23 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Landing Ellipse Azimuth : Hypanis Vallis 22 IFPA: ° IFPA: ° IFPA: ° IFPA: ° IFPA: ° Inertial Flight Path Angle [deg] Landing Ellipse Azimuth [deg]

24 This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed to any third party without the prior written permission of Thales Alenia Space -  2012, Thales Alenia Space Conclusions from Entry Corridor stand point Landing Site Entry Corridor Landing ellipse azimuth within entry corridor (LPO*) NotesPreliminary Way Forward Oxia Planum ✔ [ ° °] 97.57° 99.55°Small marginsReview constraints to increase margins Hypanis Vallis ✔ [ ° °] 91.62° 93.73°Small marginsReview constraints to increase margins Aram Dorsum ✔ [ ° °] 92.55° 93.82°Small marginsReview constraints to increase margins Mawrth Vallis TBC Investigate verticalization constraint (down to 1 km) and increase of landing accuracy LSSWS#2 Torino Dec * Results are relevant only to LPO mission scenario


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