USA-210

 2009-057A

---

DMSP 18 Launch by Atlas V 401 AV-017. Processed at LMSC/Sunnyvale. Will replace F-16.

AV-017 was used to test long duration Centaur ops and then disposed into a heliocentric orbit with C3 = 37.47 km2/s2. 5400 kg of extra LOX/LH2 was available after DMSP delivery.

DMSP 18
Date	Time	Event	Orbit
2009 Oct 18	1612:01	Launch by Atlas V 401	V SLC3E
		T+4:07 BECO
		T+4:13 Stage 1 sep
		T+4:23 MES-1
		T+4:31 Fairing sep
	1627:21	T+15:20 MECO-1
	1630	T+18:09, Centaur sep, MECO1+2:49	857 x 857 x 99
		102.8 850 x 857 x 98.8 (UN)
	1646?	T+35:00? sep+16:40 Begin Centaur demo
		AV-017 Hydrazine burn to settle prop at reduced duty cycle
		Single-direction roll coast test
		Controlled GO2 venting test
		LH2 pulsed chilldown test
	1910	T+2:58:07 Centaur MES2, disposal, 841 km
		Test of GO2 venting during engine burn
		Enhanced MRS (continue until significant thrust decrease)
	1913	T+3:01:47 Centaur MECO2, escape traj, 917 km
		T+3:05:14 Begin blowdown
		T+3:28:24 Blowdown complete
		T+3:41:04 N2H4 depletion
	1957	T+3:45:04 Centaur EOM
		T+3:55:04 get Orbital Param Message
2009 Oct 19	0108	Centaur pass EL1:4
2009 Oct 21	1400?	Centaur depart Earth L1 sphere
2016 Mar		Primary sat at 0710 LT

STS-127 (Endeavour)

 2009-038A

---

On OV-105, 3003 for Wolf and 3018 for Cassidy. No rotation with ISS EMUs.

On ISS: EMU 3005 Kopra,Marshburn with 3011 as backup. 3006 not used.

Launch mass 119939 kg and landing mass 97389 kg.

The ODS carries the DTO 701B DragonEye LIDAR nav sensor for SpaceX on the TCS mount.

On EVA-4 the astronauts removed thermal covers from the ELF-ES and then went out to the P6 IEA to replace batteries there. Only two out of a planned four were swapped out when the spacewalk was cut short as CO2 levels rose in Cassidy's suit; the LiOH canister was unable to keep up with his rapid exertions early in the EVA.

Landing mass expected 97623 kg. MD to ISS 987 kg plus 582 kg consumables, ISS to MD 898 kg. Total transfer 11176 up, 4753 down (including 1020 kg BORUs). PLB to 10189 kg up, 3855 kg down; 'Real time additions' 66 up 75 down. Down cargo includes old P6 BORUs.

After docking:

• JEM-EF is installed on JEM-PM with SSRMS.

• ICC-VLD is installed on POA (Payload ORU Accomodation) on ISS using SRMS and SSRMS.

• ICC-VLD is moved to P6 by SSRMS/SPDM for battery install/replace; then back to POA.

• PM-2, LDU, SGANT installed on ESP-3 from ICC-VLD using SSRMS, EVA.

• ICC-VLD reberthed in bay.

• ELM-ES installed on JEM-EF by SRMS/SSRMS

• SEDA,MAXI and ICS transferred from ELM-ES to JEM-EF using JEM-RMS

• ELM-ES returned to PLB using SSRMS,SRMS.

The Bay 5 ECSH contains JEM-EF LTA cable stowage The Bay 13 ECSH supports ICC-VLD LTA cable stowage

PPSU 1 (Payload power switching unit) gives power to ELM-ES; PPSU 2 gives power to ICC-VLD. The SPDU gives power to the OBSS laser sensor, and the ROEU powers the ELM-ES heaters.

The flight includes two experiments using Orbiter engine burns: MAUI (Maui analysis of upper atmospheric injections) and SEITE (Shuttle Engine Ion Turbulence Experiment).

The EVAs will generate some debris; EVA-1 will jettison the EFBM Contam Cover; EVA-2 may jettison two Vision Equipment Camera covers (if not bagged); EVA-3 will jettison three ICS-EF thermal covers.

 

STS-127
Date	Time	Event	Orbit
2009 Apr 10		Roll to VAB
2009 Jun 13	0426	T- 7h Scrub due to GUCP gas leak during tanking
2009 Jul 15	2203:10	Launch
	2205:13	SRB sep
	2205:24	OMS Ass
	2206:35	OMS ASS CO
	2211:34	T+8:30 MECO
	2211:56	ET-131 sep	58 x 230 x 51.6
	2241:40	T+38:30 OMS-2 30.1m/s 1:06?	158? x 229 x 51.6
	2242:43	OMS-2 CO
	2335:25	PLBD open	88.38 155 x 232 x 51.6
2009 Jul 16
	0147:38	OMS-3 NC1
	0147:59	OMS-3 CO
	0600		88.70 180 x 240 x 51.6
	1454:09	OMS-4 R NC2	88.75 177 x 247 x 51.6
	1454:19	OMS-4 CO
	1550?	OBSS unberth
	2200		88.78 187 x 241 x 51.6
2009 Jul 17		Rendezvous
	0400		88.80 186 x 243 x 51.6
	1300:17	OMS-5 NH 113924 kg 46 m/s
	1301:54	OMS-5 CO
	1345:32	OMS-6 NC4 27m/s 112226 kg
	1346:28	OMS-6 CO
	1420	NCC
	1517:26	OMS-7 L TI burn 12s 3m/s 111248 kg
	1517:38	OMS-7 CO
	1538	MC1
	1611	MC2
	1629	MC3
	1638	MC4
	1650	210m on Rbar nadir
	1656	Begin RPM
	1704	RPM complete
	1717	On +Vbar
	1737	Adjust alignment
	1739	Final approach from 10m
	1747:06	Docking	341 x 351 x 51.6
	1948	HO
	2122	Kopra joins EX20
2009 Jul 18	0035	15-min orbit boost, avoid object 84180
		EVA-1 Wolf, Kopra
	1320	RMS in motion
	1505?	SSRMS grappled JEM EF
	1553	Depress in progress
	1605	Resume at 5psi
	1606	2.1 psi
	1613	0.7 psi
	1618	HO	91.49 344 x 351 x 51.6
	1619	Battery power
	1626	Egress Kopra
	1630	Wolf still in AL
	1635	Egress Wolf
	1715	Active berthing mechanism MLI cover removed from JEM Kibo by Wolf
	1724	EF thermal cover removed for temp store in toolbox
	1742	JPM ABM MLI thermal cover jettisoned by Wolf
	1759	SSRMS unberth EF
	1810?	Kopra removes MAXI cover
	1830	SRMS grapples EF
	1837	MAXI cover stowed in AL?
	1846	SSRMS ungrapple EF
	1955	Wolf releasing P3 UCCAS
	1955	EF in handoff position
	2005	UCCAS released
	?	MT translate from WS6 to WS7
	2010	SSRMS walk off: grapple MBS, based on Harmony
		SSRMS ungrapple Harmony, based on MBS
	2030	SSRMS in motion
	2058	SSRMS grapple EF
	2107	SRMS ungrapple EF
	2130	Wolf ingress
	2133?	Kopra ingress
	2142	TC close
	2142	EF close to Kibo
	2148	HC
	2151	Repress NASA: 5:32
	2215?	EF mated to Kibo
	2228	EF latched
	2247	EF fully latched
	2334	EF installation complete
2009 Jul 19	1347	RMS grapple ICC-VLD
	1402	RMS unberth ICC-VLD
	1501	SSRMS ready to grapple
	1515?	SSRMS grapple ICC
	1527?	RMS ungrapple ICC
	1605	ICC near MBS POA
	1658	ICC berthed on MBS POA
	1710	SSRMS ungrapple ICC
2009 Jul 20		EVA-2 Wolf, Marshburn
	1457	At 5 psi
	1508	Depress?
	1524	HO
	1527	Battery power
	1542?	Egress Marshburn
	1545	Egress Wolf
	1730	SGANT unberthed from ICC-VLD
	1820	SGANT installed on ESP
	1920	Pump module installed on ESP
	2030	MT spare LDU drive installed on ESP
	2145?	TC open
	2205?	Ingress
	2207	TC closed
	2215	HC
	2220	Repress
2009 Jul 21
	1229	SRMS grapple JLE
	1245?	SRMS unberth JLE
	1330	SSRMS grapple JLE ("Jelly")
	1333?	SRMS ungrapple JLE
	1426	JEL soft dock with EF
	1435	SSRMS dock ELM-ES (JLE) with EF
	1535	SSRMS ungrapple JLE?
		SSRMS grapple ICC
	1650?	SSRMS unberth ICC from MBS
	1830?	MT translation to near P6
2009 Jul 22		EVA-3 Cassidy, Wolf
	1402	Begin depress
	1424	1 psi
	1428?	Depress
	1430	0.5 psi
	1431	HO
	1432	Battery power
	1439	Go for egress
	1442	Cassidy egress
	1445	Wolf egress
	1446	TC closed
	1507	JEF Thermal cover 1 jettison by Cassidy
	1516	Thermal cover 2 jettison
	1520	Thermal cover 3 jettison
	1537	Thermal cover 4 removed for return
		Translate to P6 truss
	1640	Old Bat A removed from P6
	1645?	Old Bat A stowed on temp area in P6
	1711	New Bat A removed from ICC
	1726	New Bat A installed on P6
	1734	Old Bat B removed from P6
	1755	Old Bat B installed on ICC
	1821	New Bat B removed from ICC
	1836	New Bat B installed on P6
	1852	Old Bat C removed from P6
	1926	Old Bat C on ICC
	2005	Cassidy LiOH/CO2 problem, EVA called off
	2018	Ingress Wolf
	2021	Ingress Cassidy
	2027	HC
	2031	Repress (NASA 5:59)
2009 Jul 23
	1255	JEM-RMS grapple MAXI (on JLE)
		EF vibrations due to hard grapple
	1320?	Ungrapple MAXI
	1410?	Regrapple MAXI
	1420	JEM-RMS unberth MAXI
	1525	MAXI installed on EF
	1540?	JEM RMS ungrapple MAXI
	1622	JRMS grapple IOCS
	1726	JEM RMS unberth IOCS from JLE
	1848	IOCS berthing on EF
	1858	IOCS installed on EF
	1858	JRMS ungrapple IOCS
	1940?	JRMS grapple SEDA
	2045	SEDA-AP removed from JLE by JEM RMS
	2120	SEDA-AP installed on EF
2009 Jul 24		EVA-4 Cassidy, Marshburn
	1319	Depress underway
	1339	Resume depress
	1345	Depress 0.7 psi
	1347	0.6 psi
	1353	0.5 psi
	1353	HO
	1354	Battery power
	1401	Egress Marshburn
	1408	Egress Cassidy
		Battery replacements at P6
	1435	Cassidy and Marshburn arrive at P6
	1458	New battery C removed from ICC
	1519	New battery C installed on P6
	1530	Old battery D removed from P6
	1612	Old battery D on ICC
	1645	New battery D removed from ICC
	1719	New battery D installed on P6
	1740	Old battery E removed from P6
	1810	Old battery E installed on ICC
	1833	New battery E removed from ICC
	1853	New battery E installed on P6
	1908	Old battery F removed from P6
	1924	Old battery F installed on ICC
	1942	New battery F removed from ICC
	1950	New battery F installed
	2003	Old battery A moved from P6 temp to ICC
	2025	SSRMS moving ICC away from P6
	2052	Cassidy ingress
	2055	Marshburn ingress
	2102	HC
	2107	Repress NASA 7:12
	2133	SSRMS hand ICC to SRMS
	2220	ICC being berthed by RMS in bay
	2250	ICC berthed and latched
	2258	SRMS ungrapple
2009 Jul 26
	0850?	MT move WS8 to WS4
	1150	JLE grappled by SSRMS
	1218	JLE being moved away from EF
	1257	SMRS grapple JLE
	1305	SSRMS ungrapple JLE
	1345	JLE latched in bay
	1349	SRMS ungrapple JLE
2009 Jul 27		EVA-5 Cassidy, Marshburn
	1128	1 psi
	1130?	Depress
	1132	HO
	1133	Battery power
	1142?	Egress Cassidy
	1146?	Egress Marshburn
	1220	Cassidy work on Z1 elec cables
	1230	Marshburn fix Dextre thermal covers
		Cassidy and Marshburn to EF
	1330	TV camera install on EF
	1500	TV cameras install on Kibo
	1608?	Marshburn ingress
	1616	Cassidy ingress
	1617	TC closed
	1623	HC
	1627	Repress (NASA 4:54)
		SSRMS relocate to Node 2
2009 Jul 28
	1508	Hatch closed to ISS
	1725:56	Undocking
	1726:06	RCS ISS Sep
	1730	8m sep
	1753:04	Begin flyaround on +Vbar at 130m
	1806	On R-bar zenith
	1810	Range 188m
	1817	On -Vbar
	1828	On R-bar nadir 187m
	1840	On +Vbar
	1840:40	Sep-1 6s 0.5m/s
	1908:40	Sep-2 42s 3m/s
2009 Jul 29
	1502	SRMS berth/ungrapple OBSS
	1728:43	OMS 8 both, 10s SEITE-1 burn	328 x 353
	1728:53	OMS 8 CO
	2012:09	OMS 9 L, Sep-3 11.8s Orbit adjust 3m/s	328 x 342
	2012:22	OMS 9 CO
2009 Jul 30
	1103:49	OMS-10 both, SEITE-2 burn 9.9s 5.0m/s	323 x 347
	1103:59	OMS-10 CO
	1124:09	RCS OA burn 21.7s 1.6m/s	323 x 341
	1234:30	Dragonsat deploy (MET 15:14:31:20)
	1234:35	Dragonsat Bevo/Aggiesat failed to sep
	1723:02	ANDE-2 deploy (MET 19:19:52)
	1723:39	ANDE-2 upper can sep from center
	1723:39	ANDE Passive ? sep from upper can
	1723:56	ANDE Center disk separate from lower can
	1723:56	ANDE Active sep from lower can
	1748s	SEP-4 RCS burn 2s
2009 Jul 31
	1101:41	PLBD closed	327 x 336 x 51.6
	1341:10	OMS DO 92.4m/s 2:51
	1344:01	OMS DO CO	17 x 335 x 51.6
	1416:31	EI
	1448:10	MGTD KSC RW15
	1448:21	NGTD
	1449:13	Wheels stop
	1926	OPF Bay 2

Mikhail Lomonosov

 2016-026A

---

MVL-300 (Mikhail Vasilyevich Lomonosov-300) uses Kanopus-V bus. Mission led by MGU to study high energy gamma rays. Built by VNIIEM. Launch fairing 220KS. Satellite ML10 No. 1507001. Launch from Vostochniy 371SK14 (PU No. 1S).

646 kg (625 kg?) satellite, box + 2 panels + boom. 14S46 No. 6 (No. R15000-006), Volga+adapter is 1120 kg dry 402kg prop. AIST 53 kg.

Launch by Soyuz-2-1A/Volga 372RN16 No. R15000-001. The 372RN16 was modified from the 14A14 by relocating third stage propellant drainage connectors, new unit KhIT BAS-V, new computer Malakhit-7, BKS SU, BSIUZ, radio telemetry system, high speed transponder, rocketcam?

MVL300
Date	Time	Event	Orbit
2016 Apr 28	0201:21	Launch by Soyuz-2-1A/Volga	Vostochniy
		T+1:57 BVGD sep
		T+3:41 Fairing sep
		T+4:47 Blok A sep
		T+4:49 KhO Sep
		T+4:49? Blok I burn
	0210:05	T+8:44 St 3 MECO
		T+8:48 St 3 sep	190 x 216 x 97.27
	0252:09	T+50:48 Volga burn 1 3min
	0254:42	T+53:20 Volga MECO-1	237 x 496 x 97.27
	0338:14	T+1:36 Volga MES-2 2min
	0340:26	T+1:39 MECO-2	481 x 499 x 97.27
	0406:49	T+2:05:28	Kontakt-Nanosputnik sep
	0406:59	T+2:05:38	AIST-2D, Lomonosov sep
	0818	MES-3 deorbit
	0828	MECO-3
	0854	Entry over Pacific
	0904	Debris impact

Payload:

• TUS (Tracking Ultraviolet Setup) to study UV flourescence of cosmic ray air showers in atmosphere. 6 0.58m Fresnel mirror modules, total aperture 1.4m with 1.5m focal length. (MGU/)

• BORG Block for X and Gamma detection, Gamma ray burst detectors, all-sky, 0.02-5.0 Mev

• UFFO UV/soft X camera, 0.20m aperture

• ShOK Optical wide field cameras

• DEPRON Dosimeter of electrons, protons, neutrons

Astrosat

 2015-052A

---

ISRO X-ray astronomy satellite; simultaneous UV to X continuum. Large X-ray bandwidth, slightly better UV imaging than Galex. Satellite is 1650 kg 40 kg prop (LAXPC is 350 kg?) IRS bus.

UV corr multilambda monitoring of AGN; XRBcyclotron lines and UV survey. Event list data from UVIT with aspect optical monitor from NUV beamsplitter; optical event list MCP detector. Coaligned telescope... UV is more sensitive. X-band station in Bangalore; satellite can store 4 orbits of data. Will do 6 months sky survey covering 30% of sky - galactic poles exposure to 1ks mag 20/21 and then pointed observations afterwards. 27 arcmin FOV.

Astrosat
Date	Time	Event	Orbit
2015 Sep 28	0430	Launch by PSLV-XL	SDSC LP1
		T+0:25 PSOM 5-6 on
		T+1:10 PSOM 1-2 sep
		T+1:10 PSOM 3-4 sep
		T+1:32 PSOM 5-6 sep
		T+1:52 St 1 sep
		T+1:52 St 2 on 65 km 2.3375 km/s
		T+2:49 PLF sep 114 km 2.9829 km/s
	0434	T+4:23 St 2 sep 158 km 5.2899 km/s
		T+4:24 St 3 on, 112s
	0436	T+6:16 St 3 off
	0439	T+9:48 St 3 sep 335 km, 7.5446 km/s
	0446	T+16:57 St 4 on 584 km 7.529 km/s Az 99.5
	0451	T+21:56 St 4 burnout
	0452	T+22:33 ASTROSAT sep
		LAPAN-A2 sep
	0453	T+23:28 NLS-14 (EV-9) sep
	0454	T+24:03 LEMUR-1 sep
	0454	T+24:37 LEMUR-2 sep
	0455	T+25:13 LEMUR-3 sep
	0455	T+25:33 LEMUR-4 sep
	0520?	PS3 reentry over Pacific
2015 Sep 29			97.55 633 x 650 x 6.0

Payload:

• UVIT: (IIA/IUCAA/ISRO/CSA/ ) FUV and NUV/Opt telescopes - 1200-1800 and 1800-2800A plus filters each 38cm dia, 2" res. plus small optical monitor MCP based detectors with CCD readouts.

• LAXPC Large Area Xe PropCtr 1 deg FOV - TIFR Agrwal (more area than PCA at 10-80 keV). 3 counters. The high energy response comes from more Xe column (Xe at high pressure). (TIFR/RRI/Agrawal)

• SXT :CCD on gold coated foil optics 200cm2 at 1 keV - KP Singh plus the Danish 0.2-10 keV. Tech dev for future telescopes. 0.26m dia of outermost mirror. 1.5' PSF. (TIFR/LUX/ISRO//Seeta)

• SSM Scanning Sky Monitor (coded mask and prop counter) 2-10 keV - 10 x 90 deg FOV, 10' res, 1 ms timing (ISAC/IUCAA/)

• CZTI: CdZnTe Imager, 4 coded mask telescopes and CZT arays. 10-150 keV (TIFR/IUCAA/Rao) Each of 4 bays is 16 x 16 cm. FOV 6 deg. 20' or so res

Everyday Engineering: Understanding The Marvels Of Daily Life

 https://welib.org/md5/b49f57756c702ee3534ee8774bae4715

The Right People : The Social Establishment in America

 https://welib.org/md5/0f7099af963bdae1ca05e832439413ff

The Soyuz Launch Vehicle: The Two Lives of an Engineering Triumph

https://welib.org/md5/7d00fcdc05f22a7b1ca9bef22277e7de

International directory of company histories: Volume 169

 https://welib.org/md5/4715063348fa5033c96a6d7c3355d570

SES-9

 2016-013A

---

5330 kg Boeing 702HP for East Asia, IOR maritime services and TV broadcast to NE/S Asia and Indonesia at 108.2E, with SES-7 and NSS-11. 108.2E. Launch by Falcon 9 on first GTO flight of upgraded Merlin 1D engines with 20 percent extra thrust.

SES 9
Date	Time	Event	Orbit
2016 Feb 29	0021:00	Scrub after engine ignition, T-1s
2016 Mar 4	2335:00	Launch by F9 FT	CC SLC40
		T+2:37 MECO
		T+2:40 2.5 km/s st 1 sep
		T+2:47 St 2 SEIG
		T+3:42 Fairing sep
	2344	T+9:01 SECO-1 167 km	160 x 531 x 28.5
	2345	Stage 1 braking burn
	2346	Stage 1 3-engine landing burn, impact OCISLY
2016 Mar 5	0002	T+27:07 SEIG-2
	0002	T+27:55 SECO-2
	0006	T+31:24 Stage 2 sep	730.54 334 x 40648 x 28.0
2016 Mar 9			852.97 5223 x 41606 x 14.2
2016 Mar 14			1405.61 28570 x 41805 x 0.4
2016 Mar 16			1436.19 30484 x 41092 x 0.2 GEO 119.4E
2016 Mar 25			1438.24 31087 x 40569 x 0.1 GEO 124.5E +0.5W/d
2016 Apr 13			1437.96 33628 x 38017 x 0.1
2016 Apr 22			1437.86 35076 x 36566 x 0.1
2016 Apr 28			1435.97 35678 x 35887 x 0.1 GEO 113.3E

DSCOVR

 2015-007A

---

The Deep Space Climate Observatory (DSCOVR), originally called Triana. L1 Lissajous out to 400 000 km.

Proposed by VP Al Gore, Triana would provide live TV of Earth from L1, distributed on the Internet. Mass 150 kg. Mission wass managed by NASA-GSFC as an Earth Probe, with F. Valero of Scripps/UCSD as principal investigator. Spacecraft will be a GSFC SMEX-Lite.

In the original plan, launch was to be by STS using a Star 48B stage with IUS batteries and a gyro system, deployed from the Alenia IRIS ASE. IRIS Sunshield opens 23 min before deploy. The Star 48, spinning at 60 rpm, burns 47 min after deploy for 84s for a dV of 3.2 km/s (?). 52 min after deploy GUS separates. L1 orbit achieved at 204 days. GUS was developed by GSFC. After the 10 year launch delay the spacecraft was moved to Falcon 9 and no extra upper stage was required.

Spacecraft is octagonal SMEX module with two solar arrays and cylindrical prop module.

The radiometer measures the total Earth radiation budget. The EPIC studies the vegetation canopy properties using the reflectance of the sub-solar hot spot.

Total mass 570 kg (Prop module 256 kg) with 145 kg N2H4 giving 600 m/s delta-V. Size 1.87m high 1.37m dia. 6.0m span?

DSCOVR
Date	Time	Event	Orbit
2015 Feb 11	2303:42	Launch by Falcon 9 v1.1	CC LC40
		T+2:44 MECO
		T+2:48 St 1 sep
		T+2:55 St 2 ignition
		T+3:36 Fairing sep
		T+7:35 191 km 5.615 km/s
	2312:26	T+8:44 SECO-1	184 x 186 x 36.99
	2312:42	T+9:00 St 1 landing attempt on ocean
	2333	T+30:09 St 2 burn 2 58s
	2334	T+31:07 SECO-2
	2338	T+35:08 St 2 sep	187 x 1171145 x 37.03
			187 x 1371156 x 37
2015 Feb 12	1302	Stage 2 pass EL1:4
2015 Feb 12	1312	Pass EL1:4
2015 Feb 13	0213	St 2 enter L sphere
	2037	St 2 lunar flyby	18244 x -35119 x 94.9
2015 Feb 14	1501	St2 depart L sphere
2015 Mar 4	0852	Pass GSEx=+1.2Mkm
2015 Jun		Enter L1 orbit
2016 Jan 17	0331	St 2 enter L sphere
2016 Jan 17	2003	St 2 lunar flyby	23573 x -37871 x 77.7
2016 Jan 18	1233	St2 depart L sphere

Payload:

• EPIC Earth Polychromatic Imaging Camera, 30 cm telescope with 2kx2k CCD, UV/vis/NIR.

• NISTAR Advanced radiometer (0.2-100 mu)

• PlasMag Faraday cup (Space weather monitor)

• PlasMag Magnetometer on science boom (3.5m)

• Electron spectrometer on science boom

BEAM

 2016-024

---

BEAM, Bigelow Expandable Activity Module, 1413 or 1578 kg, 3.7m l 3.2m dia; 1.75m high 2.36m dia packed. Delivered to ISS aboard Dragon CRS-8 and installed on Node 3 aft.

BEAM
Date	Time	Event	Orbit
2016 Apr 16	0500?	SSRMS grapple BEAM
	0600?	SSRMS unberth BEAM
	0620	BEAM out of CRS-8 trunk
	0900	BEAM next to N3
	0921	Ready to latch
	0937	Berthed on N3 aft (Stage 2 capture)
2016 May 25		N3 HO to BEAM vestibule opening
2016 May 26		Expand attempt, small motion 96 in to 111 in
2016 May 28	1305	113in Introduce 22s air
	1313	8s air
	1338	3s air
	1352	1s air
	1443	1s air
	1510	5s air
	1525	3s air
	1620	1s? air, 32 in long 118 dia
	1644	2s air
	1652	2s air (try 13, 54s total), 34 x 118
	1712	1s air, 35 x 119
	1724	1s air, 37 x 119
	1748	1s air 38 x 120
	1808	1s air 39 x 120
	1825	1s air 40 x 120
	1853	2s air 41 x 120
	1918	42 x 120
	1936	8s air 56 x 123
	1943	10s air (try 21) 59 x 125
	1946	14s air 63 x 127
	1950	15s air 66 x 127
	1955	30s air 66.5 x 127
	2003	9s air 67 x 127
	2010	Manual expansion declared complete
	2034	Begin pressurization
	2044	Pressurization complete
2016 Jun 6	0847	Williams and Skripochka entry

Yamal 401

 2014-082A

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Two Yamal 400 satellites built by ISS Reshetnev using the Ekspress 2000A bus with Thales Alenia Space payloads for Gazprom Space Systems. Yamal 401 at 90E for service to Russia and polar regions, Ekspress-2000.

Mass 2976 kg.

Yamal 401
Date	Time	Event	Orbit
2014 Dec 16	0016	Launch by Proton	KB LC81/24
	0018:00	St 1 sep
	0021:26	MD2 MECO
	0021:27	St 2 sep
	0021:30	MD3 burn
	0021:45	GO sep
	0025:42	MECO
	0025:42	OB sep	-449 x 170 x 51.5
	0027:16	MDU-1
	0031:22	MECO-1	171 x 173 x 51.5
	0123:28	MDU-2
	0141:22	MECO2	264 x 4996 x 49.95
	0344:57	MDU-3
	0402:58	MECO-3	383 x 35654 x 47.65
	0404:19	DTB sep
	0903:09	MDU-4
	0916:14	MECO-4	35364 x 35635 x 0.0
	0917:23	Briz sep
	1126	Briz SOZ-6
	1231	Briz SOZ-7