Template:Infobox rocket/testcases

Soyuz-U (Soyuz-U/Ikar; Soyuz-U/Fregat)
	A Soyuz-U on the launchpad in 1975 for the Apollo–Soyuz mission
Function	Orbital carrier rocket
Manufacturer	TsSKB-Progress
Country of origin	Soviet Union (Russia)
Size
Height	51.1 m for Soyuz-U; 47.3 m for Soyuz-U/Ikar and 46.7 m for Soyuz-U/Fregat
Diameter	3 m
Mass	313,000 kg (Soyuz-U); 308,000 kg (Soyuz-U/Ikar and Soyuz-U/Fregat)
Stages	2 (Soyuz-U) or 3 (Soyuz-U/Ikar and Soyuz-U/Fregat)
Capacity
Payload to LEO	6,900 kg from Baikonur and 6,700 kg from Plesetsk
Associated rockets
Family	R-7 (Soyuz)
Derivative work	Soyuz-U2; Soyuz-FG
Launch history
Status	Active
Launch sites	LC-1 & LC-31, Baikonur; LC-16 & LC-43, Plesetsk
Total launches	777
Success(es)	757
Failure(s)	21
First flight	18 May 1973
Type of passengers/cargo	Soyuz spacecraft; Progress spacecraft
Boosters – Blok-B,V,G,D
No. boosters	4
Height	19.6 m (64 ft)
Diameter	2.68 m (8.8 ft)
Empty mass	Soyuz: 3,800 kg (8,400 lb); Soyuz/ST: 3,820 kg (8,420 lb)
Gross mass	43,400 kg (95,700 lb)
Powered by	RD-117
Maximum thrust	Sea Level: 838.5 kN (188,500 lbf); Vacuum: 1,021.3 kN (229,600 lbf)
Specific impulse	Sea Level: 262 s (2.57 km/s); Vacuum: 319 s (3.13 km/s)
Burn time	118 seconds
Propellant	LOX/RG-1
First stage – Blok-A
Height	27.10 m (88.9 ft)
Diameter	2.95 m (9.7 ft)
Empty mass	Soyuz: 6,550 kg (14,440 lb); Soyuz/ST: 6,450 kg (14,220 lb)
Gross mass	Soyuz: 99,500 kg (219,400 lb); Soyuz/ST: 99,400 kg (219,100 lb)
Powered by	RD-118
Maximum thrust	Sea Level: 792.5 kN (178,200 lbf); Vacuum: 990.2 kN (222,600 lbf)
Specific impulse	Sea Level: 255 s (2.50 km/s); Vacuum: 319 s (3.13 km/s)
Burn time	290 seconds
Propellant	LOX/RG-1
Second stage – Blok-I
Height	6.70 m (22.0 ft)
Diameter	2.66 m (8.7 ft)
Empty mass	Soyuz: 2,410 kg (5,310 lb); Soyuz/ST: 2,470 kg (5,450 lb)
Gross mass	Soyuz: 25,200 kg (55,600 lb); Soyuz/ST: 25,300 kg (55,800 lb)
Powered by	RD-0110
Maximum thrust	297.9 kilonewtons (67,000 lbf)
Specific impulse	325 seconds
Burn time	270 seconds
Propellant	LOX/RG-1
Upper stage (optional) – Fregat
Height	1.5 m (4.9 ft)
Diameter	3.35 m (11.0 ft)
Empty mass	930 kg (2,050 lb)
Propellant mass	5,250 kg (11,570 lb)
Powered by	S5.92
Maximum thrust	19.85 kilonewtons (4,460 lbf)
Specific impulse	333.2 seconds
Burn time	1100 seconds
Propellant	N2O4/UDMH
Upper stage (optional) – Ikar
Height	2.56 metres (8 ft 5 in)
Diameter	2.72 metres (8 ft 11 in)
Empty mass	820 kilograms (1,810 lb)
Gross mass	3,164 kilograms (6,975 lb)
Powered by	17D61
Maximum thrust	2.94 kilonewtons (660 lbf)
Specific impulse	307 seconds
Propellant	N2O4/UDMH
	[edit on Wikidata]

Size
Height	88.8 m (291 ft)

Size
Height	88.8 m (291 ft)
	[edit on Wikidata]

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Empty

Side by side comparison

Soyuz-U

Side by side comparison

Soyuz-U (Soyuz-U/Ikar; Soyuz-U/Fregat)
A Soyuz-U on the launchpad in 1975 for the Apollo–Soyuz mission
Function	Orbital carrier rocket
Manufacturer	TsSKB-Progress
Country of origin	Soviet Union (Russia)
Size
Height	51.1 m for Soyuz-U; 47.3 m for Soyuz-U/Ikar and 46.7 m for Soyuz-U/Fregat
Diameter	3 m ^[1]
Mass	313,000 kg (Soyuz-U); 308,000 kg (Soyuz-U/Ikar and Soyuz-U/Fregat)
Stages	2 (Soyuz-U) or 3 (Soyuz-U/Ikar and Soyuz-U/Fregat)
Capacity
Payload to LEO	6,900 kg from Baikonur and 6,700 kg from Plesetsk
Associated rockets
Family	R-7 (Soyuz)
Derivatives	Soyuz-U2 Soyuz-FG
Launch history
Status	Active
Launch sites	LC-1 & LC-31, Baikonur LC-16 & LC-43, Plesetsk
Total launches	777^[3]^[4]
Success(es)	757^[5]
Failure(s)	21^[3]^[5]
First flight	18 May 1973^[2]
Notable payloads	Soyuz spacecraft Progress spacecraft

Boosters – Blok-B,V,G,D^[6]
No. boosters	4
Height	19.6 m (64 ft)
Diameter	2.68 m (8.8 ft)
Empty mass	Soyuz: 3,800 kg (8,400 lb) Soyuz/ST: 3,820 kg (8,420 lb)
Gross mass	43,400 kg (95,700 lb)
Powered by	RD-117
Maximum thrust	Sea Level: 838.5 kN (188,500 lbf) Vacuum: 1,021.3 kN (229,600 lbf)
Specific impulse	Sea Level: 262 s (2.57 km/s) Vacuum: 319 s (3.13 km/s)
Burn time	118 seconds
Propellant	LOX/RG-1
First stage – Blok-A^[6]
Height	27.10 m (88.9 ft)
Diameter	2.95 m (9.7 ft)
Empty mass	Soyuz: 6,550 kg (14,440 lb) Soyuz/ST: 6,450 kg (14,220 lb)
Gross mass	Soyuz: 99,500 kg (219,400 lb) Soyuz/ST: 99,400 kg (219,100 lb)
Powered by	RD-118
Maximum thrust	Sea Level: 792.5 kN (178,200 lbf) Vacuum: 990.2 kN (222,600 lbf)
Specific impulse	Sea Level: 255 s (2.50 km/s) Vacuum: 319 s (3.13 km/s)
Burn time	290 seconds
Propellant	LOX/RG-1
Second stage – Blok-I^[6]
Height	6.70 m (22.0 ft)
Diameter	2.66 m (8.7 ft)
Empty mass	Soyuz: 2,410 kg (5,310 lb) Soyuz/ST: 2,470 kg (5,450 lb)
Gross mass	Soyuz: 25,200 kg (55,600 lb) Soyuz/ST: 25,300 kg (55,800 lb)
Powered by	RD-0110
Maximum thrust	297.9 kilonewtons (67,000 lbf)
Specific impulse	325 seconds
Burn time	270 seconds
Propellant	LOX/RG-1
Upper stage (optional) – Fregat^[7]
Height	1.5 m (4.9 ft)
Diameter	3.35 m (11.0 ft)
Empty mass	930 kg (2,050 lb)
Propellant mass	5,250 kg (11,570 lb)
Powered by	S5.92
Maximum thrust	19.85 kilonewtons (4,460 lbf)
Specific impulse	333.2 seconds
Burn time	1100 seconds
Propellant	N₂O₄/UDMH
Upper stage (optional) – Ikar^[8]
Height	2.56 metres (8 ft 5 in)
Diameter	2.72 metres (8 ft 11 in)
Empty mass	820 kilograms (1,810 lb)
Gross mass	3,164 kilograms (6,975 lb)
Powered by	17D61
Maximum thrust	2.94 kilonewtons (660 lbf)
Specific impulse	307 seconds
Propellant	N₂O₄/UDMH

Ariane 5

Side by side comparison

Ariane 5
Size
Ariane 5 ES with ATV-4 on board on its way to the launch pad
Function	Heavy launch vehicle
Manufacturer	Airbus Defence and Space for ESA and Arianespace
Country of origin	20 ESA member states Austria Belgium Czech Republic Denmark Finland France Germany Greece Ireland Italy Luxembourg Netherlands Norway Poland Portugal Romania Spain Sweden Switzerland United Kingdom
Height	46–52 m (151–171 ft)
Diameter	5.4 m (18 ft)
Mass	777,000 kg (1,713,000 lb)
Stages	2
Capacity
Payload to LEO (260 km (162 mi) circular, 51.6˚)
Mass	G: 16,000 kg (35,000 lb) ES: over 20,000 kg (44,000 lb)^[9]
Payload to GTO
Mass	G: 6,950 kg (15,320 lb) G+: 6,950 kg (15,320 lb) GS: 6,100 kg (13,400 lb) ECA: 10,500 kg (23,100 lb)

Associated rockets
Family	Ariane
Launch history
Status	Active
Launch sites	Guiana Space Centre ELA-3
Total launches	85 (G: 16, G+: 3, GS: 6) (ECA: 55, ES: 5)
Success(es)	81 (G: 13, G+: 3, GS: 6) (ECA: 54, ES: 5)
Failure(s)	2 (G: 1, ECA: 1)
Partial failure(s)	2 (G)
First flight	G: 4 June 1996 G+: 2 March 2004 GS: 11 August 2005 ECA: 11 December 2002 ES: 9 March 2008
Last flight	G: 27 September 2003 G+: 18 December 2004 GS: 18 December 2009
Type of passengers/cargo	Rosetta Automated Transfer Vehicle Herschel Space Observatory Planck

Boosters (G, G+) – EAP P238
No. boosters	2
Height	31.6 m (104 ft)
Diameter	3.06 m (10.0 ft)
Gross mass	270 tonnes (300 tons)
Powered by	P238
Maximum thrust	6,650 kN (1,490,000 lb_f)
Total thrust	13,300 kN (3,000,000 lb_f)
Burn time	130s
Propellant	AP, Al, HTPB
Boosters (GS, ECA, ES) – EAP P241
No. boosters	2
Height	31.6 m (104 ft)
Diameter	3.06 m (10.0 ft)
Empty mass	33 tonnes (36 tons)
Gross mass	273 tonnes (301 tons)
Powered by	P241
Maximum thrust	7,080 kN (1,590,000 lb_f)
Total thrust	14,160 kN (3,180,000 lb_f)
Burn time	140s
Propellant	AP, Al, HTPB
Core stage (G, G+, GS) – EPC H158
Height	23.8 m (78 ft)
Diameter	5.4 m (18 ft)
Empty mass	12,200 kg (26,900 lb)
Gross mass	170,500 kg (375,900 lb)
Powered by	G, G+: Vulcain 1 GS: Vulcain 1B
Maximum thrust	1,015 kN (228,000 lb_f) (vacuum)
Specific impulse	440s (vacuum)
Burn time	605s
Propellant	LOX / LH₂
Core stage (ECA, ES) – EPC H173
Height	23.8 m (78 ft)
Diameter	5.4 m (18 ft)
Empty mass	14,700 kg (32,400 lb)
Gross mass	184,700 kg (407,200 lb)
Powered by	Vulcain 2
Maximum thrust	960 kN (220,000 lb_f) (sea level) 1,390 kN (310,000 lb_f) (vacuum)
Specific impulse	310s (sea level) 432 (vacuum)
Burn time	540s
Propellant	LOX / LH₂
Second stage (G) – EPS L9.7
Height	3.4 m (11 ft)
Diameter	5.4 m (18 ft)
Empty mass	1,200 kg (2,600 lb)
Gross mass	10,900 kg (24,000 lb)
Powered by	Aestus
Maximum thrust	27 kN (6,100 lb_f)
Burn time	1100
Propellant	MMH / N₂O₄
Second stage (G+, GS, ES) – EPS L10
Height	3.4 m (11 ft)
Diameter	5.4 m (18 ft)
Empty mass	1,200 kg (2,600 lb)
Gross mass	11,200 kg (24,700 lb)
Powered by	Aestus
Maximum thrust	27 kN (6,100 lb_f)
Burn time	1170
Propellant	MMH / N₂O₄
Second stage (ECA) – EPS ESC-A
Height	4.711 m (15.46 ft)
Diameter	5.4 m (18 ft)
Empty mass	4,540 kg (10,010 lb)
Gross mass	19,440 kg (42,860 lb)
Powered by	HM7B
Maximum thrust	67 kN (15,000 lb_f)
Specific impulse	446s
Burn time	945s
Propellant	LOX / LH₂

[edit on Wikidata]

Ariane 5
Ariane 5 ES with ATV-4 on board on its way to the launch pad
Function	Heavy launch vehicle
Manufacturer	Airbus Defence and Space for ESA and Arianespace
Country of origin	20 ESA member states Austria Belgium Czech Republic Denmark Finland France Germany Greece Ireland Italy Luxembourg Netherlands Norway Poland Portugal Romania Spain Sweden Switzerland United Kingdom
Size
Height	46–52 m (151–171 ft)
Diameter	5.4 m (18 ft)
Mass	777,000 kg (1,713,000 lb)
Stages	2
Capacity
Payload to LEO (260 km (162 mi) circular, 51.6˚)
Mass	G: 16,000 kg (35,000 lb) ES: over 20,000 kg (44,000 lb)^[9]
Payload to GTO
Mass	G: 6,950 kg (15,320 lb) G+: 6,950 kg (15,320 lb) GS: 6,100 kg (13,400 lb) ECA: 10,500 kg (23,100 lb)

Associated rockets
Family	Ariane
Launch history
Status	Active
Launch sites	Guiana Space Centre ELA-3
Total launches	85 (G: 16, G+: 3, GS: 6) (ECA: 55, ES: 5)
Success(es)	81 (G: 13, G+: 3, GS: 6) (ECA: 54, ES: 5)
Failure(s)	2 (G: 1, ECA: 1)
Partial failure(s)	2 (G)
First flight	G: 4 June 1996 G+: 2 March 2004 GS: 11 August 2005 ECA: 11 December 2002 ES: 9 March 2008
Last flight	G: 27 September 2003 G+: 18 December 2004 GS: 18 December 2009
Notable payloads	Rosetta Automated Transfer Vehicle Herschel Space Observatory Planck

Boosters (G, G+) – EAP P238
No. boosters	2
Height	31.6 m (104 ft)
Diameter	3.06 m (10.0 ft)
Gross mass	270 tonnes (300 tons)
Powered by	P238
Maximum thrust	6,650 kN (1,490,000 lb_f)
Total thrust	13,300 kN (3,000,000 lb_f)
Burn time	130s
Propellant	AP, Al, HTPB
Boosters (GS, ECA, ES) – EAP P241
No. boosters	2
Height	31.6 m (104 ft)
Diameter	3.06 m (10.0 ft)
Empty mass	33 tonnes (36 tons)
Gross mass	273 tonnes (301 tons)
Powered by	P241
Maximum thrust	7,080 kN (1,590,000 lb_f)
Total thrust	14,160 kN (3,180,000 lb_f)
Burn time	140s
Propellant	AP, Al, HTPB
Core stage (G, G+, GS) – EPC H158
Height	23.8 m (78 ft)
Diameter	5.4 m (18 ft)
Empty mass	12,200 kg (26,900 lb)
Gross mass	170,500 kg (375,900 lb)
Powered by	G, G+: Vulcain 1 GS: Vulcain 1B
Maximum thrust	1,015 kN (228,000 lb_f) (vacuum)
Specific impulse	440s (vacuum)
Burn time	605s
Propellant	LOX / LH₂
Core stage (ECA, ES) – EPC H173
Height	23.8 m (78 ft)
Diameter	5.4 m (18 ft)
Empty mass	14,700 kg (32,400 lb)
Gross mass	184,700 kg (407,200 lb)
Powered by	Vulcain 2
Maximum thrust	960 kN (220,000 lb_f) (sea level) 1,390 kN (310,000 lb_f) (vacuum)
Specific impulse	310s (sea level) 432 (vacuum)
Burn time	540s
Propellant	LOX / LH₂
Second stage (G) – EPS L9.7
Height	3.4 m (11 ft)
Diameter	5.4 m (18 ft)
Empty mass	1,200 kg (2,600 lb)
Gross mass	10,900 kg (24,000 lb)
Powered by	Aestus
Maximum thrust	27 kN (6,100 lb_f)
Burn time	1100
Propellant	MMH / N₂O₄
Second stage (G+, GS, ES) – EPS L10
Height	3.4 m (11 ft)
Diameter	5.4 m (18 ft)
Empty mass	1,200 kg (2,600 lb)
Gross mass	11,200 kg (24,700 lb)
Powered by	Aestus
Maximum thrust	27 kN (6,100 lb_f)
Burn time	1170
Propellant	MMH / N₂O₄
Second stage (ECA) – EPS ESC-A
Height	4.711 m (15.46 ft)
Diameter	5.4 m (18 ft)
Empty mass	4,540 kg (10,010 lb)
Gross mass	19,440 kg (42,860 lb)
Powered by	HM7B
Maximum thrust	67 kN (15,000 lb_f)
Specific impulse	446s
Burn time	945s
Propellant	LOX / LH₂

Falcon 9

Side by side comparison

Falcon 9 full thrust
Size
Launch of the first Falcon 9 full thrust flight, Falcon 9 Flight 20, carrying 11 Orbcomm satellites to orbit. The first stage was recovered at Cape Canaveral Air Force Station LZ-1 following the first successful Falcon 9 landing.
Function	Orbital launch vehicle
Manufacturer	SpaceX
Country of origin	United States^[10]
Cost per launch	$61.2M^[11]
Height	70 m (230 ft) with payload fairing^[12]
Diameter	3.66 m (12.0 ft)^[10]
Mass	541,300 kg (1,193,400 lb)^[10]
Stages	2^[10]
Capacity
Payload to LEO	13,150 kg (28,990 lb) ^[10]^[11] 10,886 kg (24,000 lb) (PAF structural limitation)^[12]
Payload to GTO	At least 5,300 kg (11,700 lb)^[13]^[14]
Launch history
Status	Active
Launch sites	Cape Canaveral SLC-40 Vandenberg SLC-4E^[11]
Total launches	3
Success(es)	3
Landings	2
First flight	22 December 2015 Orbcomm OG2 Flight 2
First stage
Engines	9 Merlin 1D^[10]
Thrust	6,806 kN (1,530,000 lb_f)^[10]
Specific impulse	Sea level: 282 s^[15] Vacuum: 311 s^[16]
Burn time	162 seconds^[10]
Propellant	subcooled LOX/chilled RP-1^[17]
Second stage
Engines	Merlin Vacuum (1D)^[10]
Thrust	934 kN (210,000 lb_f)^[18]
Specific impulse	Vacuum: 348 s^[10]
Burn time	397 seconds^[10]
Propellant	LOX/RP-1
Destroyed before launch	1
[edit on Wikidata]

Falcon 9 full thrust
Launch of the first Falcon 9 full thrust flight, Falcon 9 Flight 20, carrying 11 Orbcomm satellites to orbit. The first stage was recovered at Cape Canaveral Air Force Station LZ-1 following the first successful Falcon 9 landing.
Function	Orbital launch vehicle
Manufacturer	SpaceX
Country of origin	United States^[10]
Cost per launch	$61.2M^[11]
Size
Height	70 m (230 ft) with payload fairing^[12]
Diameter	3.66 m (12.0 ft)^[10]
Mass	541,300 kg (1,193,400 lb)^[10]
Stages	2^[10]
Capacity
Payload to LEO	13,150 kg (28,990 lb) ^[10]^[11] 10,886 kg (24,000 lb) (PAF structural limitation)^[12]
Payload to GTO	At least 5,300 kg (11,700 lb)^[13]^[14]
Launch history
Status	Active
Launch sites	Cape Canaveral SLC-40 Vandenberg SLC-4E^[11]
Total launches	3
Success(es)	3
Landings	2
First flight	22 December 2015 Orbcomm OG2 Flight 2
First stage
Engines	9 Merlin 1D^[10]
Thrust	6,806 kN (1,530,000 lb_f)^[10]
Specific impulse	Sea level: 282 s^[15] Vacuum: 311 s^[16]
Burn time	162 seconds^[10]
Propellant	subcooled LOX/chilled RP-1^[17]
Second stage
Engines	Merlin Vacuum (1D)^[10]
Thrust	934 kN (210,000 lb_f)^[18]
Specific impulse	Vacuum: 348 s^[10]
Burn time	397 seconds^[10]
Propellant	LOX/RP-1
Destroyed before launch	1

References

^ http://www.astronautix.com/lvs/soyuzu.htm Astronautix.com
^ Mark Wade (26 March 2001). "Soyuz 11A511U". Friends and Partners.
^ ^a ^b Krebs, Gunter. "Soyuz-U (11A511U)". Gunter's Space Page. Retrieved 2016-04-02.
^ Krebs, Gunter. "Soyuz-U Fregat (11A511U)". Gunter's Space Page. Retrieved 2016-04-02.
^ ^a ^b In 1983, flight Soyuz T-10a took fire on the launch pad before the end of the countdown, so it is not counted in the list of launches; this is why adding successes and failures yields 778 launches instead of 777.
^ ^a ^b ^c "Soyuz-U User's Manual" (PDF). Starsem. Retrieved 11 March 2016.
^ "Конструкция разгонного блока "Фрегат"". NPO Lavochkin (in Russian). Retrieved 10 March 2016.
^ "IKAR Upper Stage". TsSKB-Progress. Retrieved 21 December 2015.
^ "Ariane 5 ES". ESA. Retrieved 27 August 2014.
^ ^a ^b ^c ^d ^e ^f ^g ^h ⁱ ^j ^k "Falcon 9". SpaceX. Retrieved 28 September 2013.
^ ^a ^b ^c "Capabilities & Services". SpaceX. Retrieved 28 September 2013.
^ ^a ^b "Falcon 9 Launch Vehicle Payload User's Guide" (PDF). 21 October 2015. Retrieved 29 November 2015. SpaceX uses one of two PAFs on the launch vehicle, based on payload mass. The light PAF can accommodate payloads weighing up to 3,453 kg (7,612 lb), while the heavy PAF can accommodate up to 10,886 kg (24,000 lb). Payloads must comply with the mass properties limitations given in Figure 3-2.
^ Bergin, Chris (February 8, 2016). "SpaceX prepares for SES-9 mission and Dragon's return". NASA Spaceflight. Retrieved February 9, 2016. The aforementioned Second Stage will be tasked with a busy role during this mission, lofting the 5,300kg SES-9 spacecraft to its Geostationary Transfer Orbit.
^ Barbara Opall-Rome (12 October 2015). "IAI Develops Small, Electric-Powered COMSAT". DefenseNews. Retrieved 12 October 2015. At 5.3 tons, Amos-6 is the largest communications satellite ever built by IAI. Scheduled for launch in early 2016 from Cape Canaveral aboard a Space-X Falcon 9 launcher, Amos-6 will replace Amos-2, which is nearing the end of its 16-year life.
^ "Falcon 9". SpaceX. Archived from the original on 1 May 2013. Retrieved 29 September 2013.
^ Ahmad, Taseer; Ammar, Ahmed; Kamara, Ahmed; Lim, Gabriel; Magowan, Caitlin; Todorova, Blaga; Tse, Yee Cheung; White, Tom. "The Mars Society Inspiration Mars International Student Design Competition" (PDF). Mars Society. Retrieved 24 October 2015.
^ Elon Musk [@elonmusk] (2015-12-17). "-340 F in this case. Deep cryo increases density and amplifies rocket performance. First time anyone has gone this low for O2. [RP-1 chilled] from 70F to 20 F" (Tweet). Retrieved 19 December 2015 – via Twitter.
^ Clark, Stephen (2016-01-25). "Falcon 9 upgrade receives blessing from U.S. Air Force". SpaceflightNow. Retrieved 2016-01-26.

[1] ttp://www.astronautix.com/lvs/soyuzu.htm Astronautix.com

[mwade-2] Mark Wade (26 March 2001). "Soyuz 11A511U". Friends and Partners.

[gunter-soyuz-u-3] Krebs, Gunter. "Soyuz-U (11A511U)". Gunter's Space Page. Retrieved 2016-04-02.

[gunter-soyuz-u-fregat-4] Krebs, Gunter. "Soyuz-U Fregat (11A511U)". Gunter's Space Page. Retrieved 2016-04-02.

[explain-launch-counts-5] In 1983, flight Soyuz T-10a took fire on the launch pad before the end of the countdown, so it is not counted in the list of launches; this is why adding successes and failures yields 778 launches instead of 777.

[starsem-6] "Soyuz-U User's Manual" (PDF). Starsem. Retrieved 11 March 2016.

[lavochkin-fregat-7] "Конструкция разгонного блока "Фрегат"". NPO Lavochkin (in Russian). Retrieved 10 March 2016.

[8] "IKAR Upper Stage". TsSKB-Progress. Retrieved 21 December 2015.

[ESAA5ES-9] "Ariane 5 ES". ESA. Retrieved 27 August 2014.

[spacex-falcon9-10] ^ ^a ^b ^c ^d ^e ^f ^g ^h ⁱ ^j ^k "Falcon 9". SpaceX. Retrieved 28 September 2013.

[spacex-capabilities-11] "Capabilities & Services". SpaceX. Retrieved 28 September 2013.

[spx-user-guide-12] "Falcon 9 Launch Vehicle Payload User's Guide" (PDF). 21 October 2015. Retrieved 29 November 2015. SpaceX uses one of two PAFs on the launch vehicle, based on payload mass. The light PAF can accommodate payloads weighing up to 3,453 kg (7,612 lb), while the heavy PAF can accommodate up to 10,886 kg (24,000 lb). Payloads must comply with the mass properties limitations given in Figure 3-2.

[nsf20160208-13] Bergin, Chris (February 8, 2016). "SpaceX prepares for SES-9 mission and Dragon's return". NASA Spaceflight. Retrieved February 9, 2016. The aforementioned Second Stage will be tasked with a busy role during this mission, lofting the 5,300kg SES-9 spacecraft to its Geostationary Transfer Orbit.

[defensenews20151012-14] Barbara Opall-Rome (12 October 2015). "IAI Develops Small, Electric-Powered COMSAT". DefenseNews. Retrieved 12 October 2015. At 5.3 tons, Amos-6 is the largest communications satellite ever built by IAI. Scheduled for launch in early 2016 from Cape Canaveral aboard a Space-X Falcon 9 launcher, Amos-6 will replace Amos-2, which is nearing the end of its 16-year life.

[15] "Falcon 9". SpaceX. Archived from the original on 1 May 2013. Retrieved 29 September 2013.

[msF9Study-16] Ahmad, Taseer; Ammar, Ahmed; Kamara, Ahmed; Lim, Gabriel; Magowan, Caitlin; Todorova, Blaga; Tse, Yee Cheung; White, Tom. "The Mars Society Inspiration Mars International Student Design Competition" (PDF). Mars Society. Retrieved 24 October 2015.

[musk-tweet-20151217-17] Elon Musk [@elonmusk] (2015-12-17). "-340 F in this case. Deep cryo increases density and amplifies rocket performance. First time anyone has gone this low for O2. [RP-1 chilled] from 70F to 20 F" (Tweet). Retrieved 19 December 2015 – via Twitter.

[sfn20160125-18] Clark, Stephen (2016-01-25). "Falcon 9 upgrade receives blessing from U.S. Air Force". SpaceflightNow. Retrieved 2016-01-26.

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