Echostar 8

 2002-039A

---

Echostar VIII is an FS-1300 satellite with a launch mass of 4685 kg. Launch by Proton-K/DM to 110W.

Stage 3 impacts the Pacific at 24 23N 161 46E.

Echostar 8
Date	Time	Event	Orbit
2002 Aug 22	0515	Launch by Proton-K/DM3 No. 20L	KB PL81/23
		T+2:03 St 1 sep
		T+5:31 St 2 sep
		T+5:37 St 3 burn
		T+5:42 Fairing sep
		T+9:33 St 3 MECO
		T+9:43 St 3 VECO
	0524:44	T+9:44 Stage 3 sep	-629? x 160 x 51.6
	0530:46	T+15:46 DM MES-1 67s
	0531:53	T+16:53 DM MECO-1	160 x 161 x 51.6
	0540?	St 3 reentry
	0627:43	T+1:12:43 DM MES-2 437s
	0635:00	T+1:20:00 DM MECO-2	167 x 35902 x 51.6?
			144 x 35809 x 51.7 (TLE)
	1129:13	T+6:14:13 DM MES-3 99s
	1130:52	T+6:15:52 DM MECO-3	4300 x 35776 x 23.0
	1150:52	T+6:35:52 S/C sep
	1335:52	T+8:20:52 DM CCAM burn
	1340:52	T+8:25:52 DM MECO-4
2002 Aug 22			712.81 4265 x 35843 x 23.0
2002 Aug 23	2330?	LAM-1
2002 Aug 24			858.96 11267 x 35841 x 11.0
2002 Aug 25	1830?	LAM-2
2002 Aug 26			985.48 17006 x 35844 x 6.4
2002 Aug 27	0330?	LAM-3
2002 Aug 28			1403.42 34470 x 35818 x 0.2
2002 Aug 29	0200?	LAM-4
2002 Aug 29			1436.90 35773 x 35830 x 0.1 GEO 129W
2002 Sep 18		mv out GEO 129W
2002 Oct 4		mv in GEO 110W
2002 Oct 5			1436.03 35775 x 35794 x 0.0 GEO 110W
2006 Aug 7			1436.08 35772 x 35800 x 0.0 GEO 110.0W
2008 Oct 31		Move to 77W
2009 Jan 3			1436.10 35778 x 35795 x 0.0 GEO 77.0W
2017 Apr 19			1436.08 35774 x 35799 x 1.0 GEO 76.9W

ExoMars

 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

2016-017

---

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)

Amazing Stories of the Space Age : True Tales of Nazis in Orbit, Soldiers on the Moon, Orphaned Martian Robots, and Other Fascinating Accounts From the Annals of Spaceflight

 https://welib.org/md5/d132ef06fc591801c3df8e9e87b994eb

Olimp-K

 2014-058A

---

Olimp-K, ISS Resehtnev satellite, given cover name Luch. According to Kommersant newspaper, http://www.kommersant.ru/doc/2436687 on 2014 Mar 24, the satellite carried electronic intelligence and communications payloads for the FSB.

Originally named Kosmos-2501 but then (by early 2015) the Kosmos name was retracted and the succeeding Glonass launch became 2501.

Olimp
Date	Time	Event	Orbit
2014 Sep 27	2023	Launch by Proton-M	KB LC81/24
	2032	Stage 3 sep
	2033	Briz MES-1
	2038?	Briz MECO-1	180 x 180?
	2130?	Briz MES-2
	2148?	Briz MECO-2	200 x 5000? x 50?
	2353?	Briz MES-3
2014 Sep 28	0002?	Perigee
	0010?	Briz MECO-3	498 x 35684 x 46.4
	0011?	DTB sep
	0511?	MES-4
	0523?	MECO-4
2014 Sep 28	0526	Sep from Briz
2014 Sep 29			1430.50 35589 x 35764 x 0.0 GEO 57.0E+1.4E/d
2014 Oct 2		Briz orbit	1571.10 35688 x 41089 x 0.1
2014 Oct 6			1433.19 35650 x 35809 x 0.0
2014 Oct 18		Location 1: 54E	1436.39 35783 x 35800 x 0.0 GEO 54.0E
2014 Dec 18			1436.05 35785 x 35786 x0.1 GEO 54.0E
2014 Dec 28		Move out from 54E
2015 Jan 2		Location 2: Move in at 52.9E	1436.11 35774 x 35798 x 0.0 GEO 52.9E
2015 Jan 28		Move out from 53E
2015 Feb 21		Location 3: Move in at 96E	1436.18 35787 x 35788 x 0.1 GEO 96.4E
2015 Mar 24			1436.22 35784 x 35793 x 0.0 GEO 96.1E
2015 Apr 4		Move out from 96E
2015 Jun 26		Location 4: Move in at 18W
2015 Sep 10			1436.06 35772 x 35799 x 0.1 GEO 18.2W
2015 Sep 24			1436.09 35773 x 35800 x 0.0 GEO 18.1W
2015 Sep 25		Move out
2015 Oct 5		Location 5: Move in at 24.3W
2015 Dec 8		Move out
2016 Jan 9		Location 6: Move in at 1.1W
2016 Aug 30		Move out
2016 Sep 14		Location 7: Move in at 9.9E
2017 Jul 27		Move out
2017 Aug 17		Location 8: Move in at 32.7E

IRNSS-1H

 2017-051A

---

The payload fairing failed to separate, causing the satellite to remain attached to the rocket in a lower than planned transfer orbit.

IRNSS-1H
Date	Time	Event	Orbit
2017 Aug 31	1330	Launch by PSLV-XL C33	SHAR SLP
		T+0:25 PSOM5,6 on
		T+1:10 SOM 1,2 sep
		T+1:10 SOM 3,4 sep
		T+1:32 SOM 5,6 sep
		T+1:51 St 1 sep 56 km
		T+1:51 St 2 burn
		T+3:23 Fairing failed to sep
	1334	T+4:23 St 2 sep
		T+4:24 St 3 burn 112s
	1336	T+6:25 St 3 burnout 91E 11N? 139.4 km 6.96km/srel
	1340	T+10:06 St 3 sep 163 km 7.7356 km/s
	1340	T+10:16 St 4 burn 186 km 7.7335 km/s
	1348	T+18:48 St 4 MECO 455 km 9.6388 km/s
	1349	T+19:25 St 4 sep	159.23 163 x 6540 x 19.2
	?	Stage 3 impact near Borneo or N Guinea?
2017 Sep 20			156.96 157 x 6364 x 19.2
2017 Nov 27			149.22 155 x 5727 x 19.2