2016-017A
ESA Aurora Flagship program mission. ExoMars will have the Trace Gas Orbiter (box + 2 panels) and descent module (cone-cylinder) containing a 20 kg rover.
TAS-I/Torino prime with Thales Alenia TAS-F/Cannes bus and integration; Ruag Space MSA.
C3=7.45? corresponds to around 5600 kg to escape including emtpy Briz. Consistent with 4400 kg TGO and 1200 kg Briz.
After cruise, TGO ejects the lander, performs MOI, and then aerobrakes to a 400 km x 74 deg orbit. TGO launch mass 4332 kg including EDM. Size 3.2 x 2 x 2m with 17.5m span
Arrival at Mars with C3 = 10.60 to 12.00 km**2/s**2; daylight prograde entry.
The DSM targets for Mars; pre the DSM both Briz and EXM are biased away.
| ExoMars | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2016 Mar 14 | 0931:42 | Launch by Proton 93560/99560 | |
| 0933:42 | St 1 sep | ||
| 0937:12 | St 2 sep | ||
| 0937:27 | T+5:45 GO sep | ||
| T+9:31 St 3 MECO | |||
| 0941:24 | T+9:42 St 3 sep | ||
| 0942:58 | T+11:16 Briz MES-1 4:29 | ||
| 0947:28 | T+15:45 Briz MECO-1 | 185 x 185 x 51.5 | |
| 1109:46 | T+1:38 MES-2 raise apo 18:03 | ||
| 1127:49 | T+1:39 MECO-2 | 250 x 5800 | |
| 1231 | Apogee | ||
| 1323:58 | MES-3 raise apo 14:31 | ||
| 1338:29 | MECO-3 | ||
| 1339 | T+4:08 DTB sep | 376.43 696 x 21086 x 51.6 | |
| 1625 | Apogee | ||
| 1947:52 | T+10:16 MES-4 raise apo 12:29 | ||
| 2000:21 | T+10:19 MECO-4 SOI | ||
| 2013:01 | T+10:41:19 Briz sep C3= 13.78 | 750 x -71355 x 51.51 | |
| 2128 | T+11:57:45 Malindi AOS | ||
| 2142 | Status confirm? | ||
| 2040? | Briz-M avoidance burns | ||
| 2016 Mar 15 | 0300? | Debris observed around Briz-M | |
| 2016 Mar 15 | 0414 | Pass EL1:4 | |
| 2016 Mar 15 | 2000? | Pass lunar orbit | |
| 2016 Mar 19 | 0428 | Exit Earth L1 sphere | |
| 2016 Jul 18 | 1100 | DSM-0 Test burn 1m/s | |
| 2016 Jul 28 | 0930 | DSM-1 52 min 420 kg, 334.2m/s | |
| 2016 Aug 11 | 0930 | DSM-2 17.7m/s 155s | |
| 2016 Oct 11 | 2315 | Briz inside Mars sphere | |
| 2016 Oct 13 | 2052 | Briz flyby | 899251 x -912424 x 5.4 |
| 2016 Oct 14 | 0845 | TCM 0.014m/s 60s | |
| 2016 Oct 15 | 1830 | Briz outside Mars sphere | |
| 2016 Oct 16 | 0110 | In Mars L1 sphere | |
| 1431:40 | LOS for sep turn | ||
| 2016 Oct 16 | 1442 | EDM/TGO sep | |
| 2016 Oct 17 | 0242 | ORM (Orbit retargeting mvr) TGO retarget burn 1:46 11.6m/s | |
| 2016 Oct 19 | 1304:47 | TGO MOI, 4-sol period, 250 km x 95900 139min | |
| 1523 | MOI MECO, 2hr, 1370?m/s | ||
| 2016 Oct 26 | 318 x 95521 x 9.5 | ||
| 2016 Oct 27? | Reduce period to 1 sol, ALM 130m/s | ||
| 2016 Nov 15 | 272 x 95570 x 9.1 | ||
| 2016 Dec 10 | 254 x 95548 x 8.4 | ||
| 2017 Jan 1 | 271 x 98435 x 7.8 | ||
| 2017 Jan 18 | 320 x 98370 x 7.3 | ||
| 2017 Jan 19 | Inc change | 596 x 98382 x 23.8 | |
| 2017 Jan 23 | Inc change | 553 x 98369 x 56.6 | |
| 2017 Jan 27 | 553 x 98391 x 56.5 | ||
| 2017 Jan 28 | Inc change | 247 x 98388 x 72.9 | |
| 2017 Feb 3 | 241 x 98311 x 72.7 | ||
| 2017 Feb 11 | 203 x 98215 x 73.9 | ||
| 2017 Feb 11 | Lower apo | 201 x 34912 x 73.9 | |
| 2017 Feb 17 | 202 x 34860 x 74.0 | ||
| 2017 Feb 18 | Lower apo | 202 x 33205 x 74.0 | |
| 2017 Mar 3 | 201 x 33322 x 74.1 | ||
| 2017 Mar 15 | 201 x 33372 x 74.0 | ||
| 2017 Mar 15 | 1156 | PLM-1 Begin aerobraking 3m/s 150 x 33350 x 74.0 | |
| 2017 Mar 18 | 1145 | PLM-2 | 135 x 33124 x 74.0 |
| 2017 Mar 21 | PLM-3 | 125 x 33090 x 74.0 | |
| 2017 Mar 24 | PLM-4 | 119 x 33002 x 74.0 | |
| 2017 Mar 27 | PLM-5 | 118 x 32845 x 74.0 | |
| 2017 Apr 1 | PLM-6 | 118 x 32520 x 74.0 | |
| 2017 Apr 9 | PLM-7 | 114 x 32201 x 74.0 | |
| 2017 Apr 11 | 112 x 31985 x 74.0 | ||
| 2017 Apr 16 | 110 x 31808 x74.0 | ||
| 2017 Apr 27 | 104 x 31151 x 73.9 | ||
| 2017 May 5 | 98 x 30004 x 73.9 | ||
| 2017 Jun 6 | 98 x 24144 x 73.9 | ||
| 2017 Jun 25 | 97 x 20930 x 73.8 | ||
| 2017 Jun 25 | Raise peri to 200 km, pause aerobrake | 200 x 20907 x 73.8 | |
| 2017 Jul 7 | 199 x 20927 x 73.9 | ||
| 2017 Aug 28 | 195 x 20929 x 73.9 | ||
| 2017 Aug 30 | 0553 | DV 5.3m/s Lower peri to 140 km | |
| 130 x 20934 x 73.8 | |||
| 2017 Sep 4 | 116 x 20932 x 73.9 | ||
| 2017 Sep 8 | 105 x 20859 x 73.9 | ||
| 2017 Sep 15 | 99 x 20102 x 73.9 | ||
| 2017 Oct 13 | 96 x 15342 x 74.0 | ||
| 2017 Oct 19 | 96 x 14505 x 74.0 | ||
| 2017 Oct 19 | FRM (Flux reduction mvr) | 9h30m | |
| 2017 Oct 27 | 92 x 12981 x 74.0 | ||
| 2017 Nov 10 | 90 x 10242 x 73.8 | ||
| 2017 Nov 24 | 93 x 8708 x 73.7 | ||
| 2017 Dec 27 | 90 x 5658 x 73.6 | ||
| 2017 Dec 31 | 85 x 5332 x 73.7 | ||
| 2018 Jan 24 | 84 x 3281 x 73.7 | ||
| 2018 Mar | Complete aerobraking | 100 x 400 | |
| Raise perapsis | 400 x 400 | ||
| 2017 Dec | Begin science mission | ||
Payload:
- Comm relay package for NASA and ESA missions
- ACS Atmospheric Chemistry Suite (IKI/Korablev), IR spectra, solar occ and nadir obs with MIR, NIR echelle and TIR Fourier spectrometers
- CaSSIS Color and Stereo Surface Imaging Syste, 5 m res camera (Bern/Thomas), 9 km swath
- FREND Fine resolution Epithermal neutron detector (IKI/Mitrofanov)
- NOMAD Nadir and occultation for Mars Discovery (IASB/Vandaele), two IR and one UV spectrometer
- 400N (424N?) S400-15 main engine MMH/MON-1, Isp =330?
- 20 x 10N S10-18 thrusters
EDM is EDL Demo Module (EDL is Entry, Descent and Landing). Launch with TGO. Will verify technologies for landing a future ESA Mars rover. Built at TAS-F and TAS-I. Management by Thales Alenia TAS-I/Torino?
Pre 2011 plan was based on TAS-F Spacebus with LEROS-1b.
Arrival at Ls=244.7.
Entry at 5N 17W. Target 6.1W 1.9S on Meridiani Planum Observed by MRO at 353.79E 2.07S (6.11W 2.07S)
Heat shield is 1.26km E 0.60km N. Backshell/para is 0.16km E 0.91km S.
Inertial entry conditions (2011 plan) 5.91 to 6.03 km/s. Relative entry 5.66 to 5.78 km/s. FPA -12.4 deg.
The lander (EDM Surface Platform, or EDP) performs a backshell avoidance manuever to land 30 to 500m short of the parachute/backshell (BCV) depending on wind.
| EDM mass budget | |
| Component | mass/kg |
| SP Lander | 280 kg |
| Hydrazine | 46 kg |
| FS Front shield | 274-x1-x2 kg |
| Parachute | x1 |
| BCV Back Cover | x2 |
| Total EDM | 600 kg |
| TGO module | 1365 kg |
| MSA Main Sep Assy | 41 |
| MMH prop | 937 |
| MON prop | 1499 |
| Residual | -110 kg |
| Total TGO/EDM | 4332 kg |
Entry mass 600 kg full including 46 kg of hydrazine. Aeroshell is cone 2.4m dia
1.32m high (FS=0.4? BS=0.9?). 70 deg sphere-cone. EADS CASA Espacio structure with ASTRIUM-ST TPS from St-Medard-en-Jalles. Backshell is 47 deg cone; Structure by TAS-F covered with ASTRIUM-ST TPS. lander is 0.5?h 1.65m dia. Disk-Gap-Band parachute 12m dia, trailing by 27m. including 1.6m drogue. Schiaparelli will separate from TGO three days before MOI. Descent uses an aeroshell, supersonic parachutes and braking thrusters which fire from 1.3 km to 2m in altitude. The lander is surrounded by a crushable carbon-fibre shell. Parachute is Huygens type.
FS is 80 kg. Rear shield is 20 kg.
Target is 1.9S 6.1W or 1.82S 6.15W.
In the event, the IMU designed to measure roll rate saturated soon after parachute deployment. The erroneous data was used to calculate the probe's altitude and the probe concluded it was already below the surface - it then prematurely jettisoned the backshell and parachutes and crashed to the surface, falling from an altitude of 3.7 km.
| EXM-EDM | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2016 Oct 16 | 1442:00 | E-3d Sep from TGO | |
| 2016 Oct 19 | 1329:48 | E-few hr Activation | |
| E=0 122.5km, 5.70-5.83 km/s vrel | |||
| 1442:22 | E=0 hsph=126.15km, Vrel = 5.86 km/s, angle -11.9 deg | ||
| Entry phase | |||
| E+1:30 Max heating 44 km | |||
| E+1:50 Max g-load, 35 km | |||
| 1445:23 | E+3:01 11 km para deploy, 0.46 km/s, 10.3 km, angle -26.6 deg | ||
| 1446:03 | E+3:57 6.85 km Front heatshield sep | ||
| Doppler altimeter on, radar acq | |||
| 1446:49 | E+4:27 4.3 km Rear heatshield and para sep, premature | ||
| 1446:51 | E+4:31 3.7 km Thrusters on | ||
| 1446:54 | E+4:34 Thrusters off,(meant to be 2 m alt) | ||
| 1447:28 | E+5:04 Impact at 150 m/s | ||
| Planned sequence | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| E+4:04 11 km para deploy, 0.46 km/s, 10.3 km, angle -26.6 deg | |||
| E+4:32 6.85 km Front heatshield sep | |||
| Doppler altimeter on, radar acq | |||
| E+5:50 1.3 km Rear heatshield and para sep 75 m/s | |||
| BAM Backshell avoidance mvr | |||
| Thrusters on - 3 s burn | |||
| 1448 | E+6:20? Touchdown on Meridiani Planum, 3 m/s | ||
| Sol 8: end of mission | |||
Payload:
- DECA Descent Camera
- DREAMS Dust characterization, Risk assessment, Environment Analyser on the Martian Surface.
- MetWind, wind vector
- DREAMS-H humidity
- DREAMS-P pressure
- SIS Solar Irradiance Sensor, atmospheric transparency
- MicroARES Atmospheric Radiation and Electricity Sensor, E field
- AMELIA Entry and descent engineering data
- COMARS+, heat flux on back cover BCV
- Laser retroreflector array
- Nine 400N engines: 3 clusters of 3 PWM (pulse width modulated) CHT400 engines on Surface Platform. (CHT400 used on Ariane 5)
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