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Template:Infobox rocket/testcases

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Size
Height88.8 m (291 ft)
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Size
Height88.8 m (291 ft)


Soyuz-U edit

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Soyuz-U (Soyuz-U/Ikar; Soyuz-U/Fregat)
A Soyuz-U on the launchpad in 1975 for the Apollo–Soyuz mission
FunctionOrbital carrier rocket
ManufacturerTsSKB-Progress
Country of originSoviet Union (Russia)
Size
Height51.1 m for Soyuz-U; 47.3 m for Soyuz-U/Ikar and 46.7 m for Soyuz-U/Fregat
Diameter3 m [1]
Mass313,000 kg (Soyuz-U); 308,000 kg (Soyuz-U/Ikar and Soyuz-U/Fregat)
Stages2 (Soyuz-U) or 3 (Soyuz-U/Ikar and Soyuz-U/Fregat)
Capacity
Payload to LEO6,900 kg from Baikonur and 6,700 kg from Plesetsk
Associated rockets
FamilyR-7 (Soyuz)
Derivative workSoyuz-U2
Soyuz-FG
Launch history
StatusActive
Launch sitesLC-1 & LC-31, Baikonur
LC-16 & LC-43, Plesetsk
Total launches777[3][4]
Success(es)757[5]
Failure(s)21[3][5]
First flight18 May 1973[2]
Type of passengers/cargoSoyuz spacecraft
Progress spacecraft
Boosters – Blok-B,V,G,D[6]
No. boosters4
Height19.6 m (64 ft)
Diameter2.68 m (8.8 ft)
Empty massSoyuz: 3,800 kg (8,400 lb)
Soyuz/ST: 3,820 kg (8,420 lb)
Gross mass43,400 kg (95,700 lb)
Powered byRD-117
Maximum thrustSea Level: 838.5 kN (188,500 lbf)
Vacuum: 1,021.3 kN (229,600 lbf)
Specific impulseSea Level: 262 s (2.57 km/s)
Vacuum: 319 s (3.13 km/s)
Burn time118 seconds
PropellantLOX/RG-1
First stage – Blok-A[6]
Height27.10 m (88.9 ft)
Diameter2.95 m (9.7 ft)
Empty massSoyuz: 6,550 kg (14,440 lb)
Soyuz/ST: 6,450 kg (14,220 lb)
Gross massSoyuz: 99,500 kg (219,400 lb)
Soyuz/ST: 99,400 kg (219,100 lb)
Powered byRD-118
Maximum thrustSea Level: 792.5 kN (178,200 lbf)
Vacuum: 990.2 kN (222,600 lbf)
Specific impulseSea Level: 255 s (2.50 km/s)
Vacuum: 319 s (3.13 km/s)
Burn time290 seconds
PropellantLOX/RG-1
Second stage – Blok-I[6]
Height6.70 m (22.0 ft)
Diameter2.66 m (8.7 ft)
Empty massSoyuz: 2,410 kg (5,310 lb)
Soyuz/ST: 2,470 kg (5,450 lb)
Gross massSoyuz: 25,200 kg (55,600 lb)
Soyuz/ST: 25,300 kg (55,800 lb)
Powered byRD-0110
Maximum thrust297.9 kilonewtons (67,000 lbf)
Specific impulse325 seconds
Burn time270 seconds
PropellantLOX/RG-1
Upper stage (optional) – Fregat[7]
Height1.5 m (4.9 ft)
Diameter3.35 m (11.0 ft)
Empty mass930 kg (2,050 lb)
Propellant mass5,250 kg (11,570 lb)
Powered byS5.92
Maximum thrust19.85 kilonewtons (4,460 lbf)
Specific impulse333.2 seconds
Burn time1100 seconds
PropellantN2O4/UDMH
Upper stage (optional) – Ikar[8]
Height2.56 metres (8 ft 5 in)
Diameter2.72 metres (8 ft 11 in)
Empty mass820 kilograms (1,810 lb)
Gross mass3,164 kilograms (6,975 lb)
Powered by17D61
Maximum thrust2.94 kilonewtons (660 lbf)
Specific impulse307 seconds
PropellantN2O4/UDMH
[edit on Wikidata]
Soyuz-U (Soyuz-U/Ikar; Soyuz-U/Fregat)
A Soyuz-U on the launchpad in 1975 for the Apollo–Soyuz mission
FunctionOrbital carrier rocket
ManufacturerTsSKB-Progress
Country of originSoviet Union (Russia)
Size
Height51.1 m for Soyuz-U; 47.3 m for Soyuz-U/Ikar and 46.7 m for Soyuz-U/Fregat
Diameter3 m [1]
Mass313,000 kg (Soyuz-U); 308,000 kg (Soyuz-U/Ikar and Soyuz-U/Fregat)
Stages2 (Soyuz-U) or 3 (Soyuz-U/Ikar and Soyuz-U/Fregat)
Capacity
Payload to LEO6,900 kg from Baikonur and 6,700 kg from Plesetsk
Associated rockets
FamilyR-7 (Soyuz)
DerivativesSoyuz-U2
Soyuz-FG
Launch history
StatusActive
Launch sitesLC-1 & LC-31, Baikonur
LC-16 & LC-43, Plesetsk
Total launches777[3][4]
Success(es)757[5]
Failure(s)21[3][5]
First flight18 May 1973[2]
Notable payloadsSoyuz spacecraft
Progress spacecraft
Boosters – Blok-B,V,G,D[6]
No. boosters4
Height19.6 m (64 ft)
Diameter2.68 m (8.8 ft)
Empty massSoyuz: 3,800 kg (8,400 lb)
Soyuz/ST: 3,820 kg (8,420 lb)
Gross mass43,400 kg (95,700 lb)
Powered byRD-117
Maximum thrustSea Level: 838.5 kN (188,500 lbf)
Vacuum: 1,021.3 kN (229,600 lbf)
Specific impulseSea Level: 262 s (2.57 km/s)
Vacuum: 319 s (3.13 km/s)
Burn time118 seconds
PropellantLOX/RG-1
First stage – Blok-A[6]
Height27.10 m (88.9 ft)
Diameter2.95 m (9.7 ft)
Empty massSoyuz: 6,550 kg (14,440 lb)
Soyuz/ST: 6,450 kg (14,220 lb)
Gross massSoyuz: 99,500 kg (219,400 lb)
Soyuz/ST: 99,400 kg (219,100 lb)
Powered byRD-118
Maximum thrustSea Level: 792.5 kN (178,200 lbf)
Vacuum: 990.2 kN (222,600 lbf)
Specific impulseSea Level: 255 s (2.50 km/s)
Vacuum: 319 s (3.13 km/s)
Burn time290 seconds
PropellantLOX/RG-1
Second stage – Blok-I[6]
Height6.70 m (22.0 ft)
Diameter2.66 m (8.7 ft)
Empty massSoyuz: 2,410 kg (5,310 lb)
Soyuz/ST: 2,470 kg (5,450 lb)
Gross massSoyuz: 25,200 kg (55,600 lb)
Soyuz/ST: 25,300 kg (55,800 lb)
Powered byRD-0110
Maximum thrust297.9 kilonewtons (67,000 lbf)
Specific impulse325 seconds
Burn time270 seconds
PropellantLOX/RG-1
Upper stage (optional) – Fregat[7]
Height1.5 m (4.9 ft)
Diameter3.35 m (11.0 ft)
Empty mass930 kg (2,050 lb)
Propellant mass5,250 kg (11,570 lb)
Powered byS5.92
Maximum thrust19.85 kilonewtons (4,460 lbf)
Specific impulse333.2 seconds
Burn time1100 seconds
PropellantN2O4/UDMH
Upper stage (optional) – Ikar[8]
Height2.56 metres (8 ft 5 in)
Diameter2.72 metres (8 ft 11 in)
Empty mass820 kilograms (1,810 lb)
Gross mass3,164 kilograms (6,975 lb)
Powered by17D61
Maximum thrust2.94 kilonewtons (660 lbf)
Specific impulse307 seconds
PropellantN2O4/UDMH

Ariane 5 edit

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{{Infobox rocket}}{{Infobox rocket/sandbox}}
Ariane 5
Ariane 5 ES with ATV-4 on board on its way to the launch pad
FunctionHeavy launch vehicle
ManufacturerAirbus Defence and Space for
ESA and Arianespace
Country of origin
20 ESA member states
Size
Height46–52 m (151–171 ft)
Diameter5.4 m (18 ft)
Mass777,000 kg (1,713,000 lb)
Stages2
Capacity
Payload to LEO (260 km (162 mi) circular, 51.6˚)
MassG: 16,000 kg (35,000 lb)
ES: over 20,000 kg (44,000 lb)[9]
Payload to GTO
MassG: 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
FamilyAriane
Launch history
StatusActive
Launch sitesGuiana Space Centre ELA-3
Total launches85
(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 flightG: 4 June 1996
G+: 2 March 2004
GS: 11 August 2005
ECA: 11 December 2002
ES: 9 March 2008
Last flightG: 27 September 2003
G+: 18 December 2004
GS: 18 December 2009
Type of passengers/cargoRosetta
Automated Transfer Vehicle
Herschel Space Observatory
Planck
Boosters (G, G+) – EAP P238
No. boosters2
Height31.6 m (104 ft)
Diameter3.06 m (10.0 ft)
Gross mass270 tonnes (300 tons)
Powered byP238
Maximum thrust6,650 kN (1,490,000 lbf)
Total thrust13,300 kN (3,000,000 lbf)
Burn time130s
PropellantAP, Al, HTPB
Boosters (GS, ECA, ES) – EAP P241
No. boosters2
Height31.6 m (104 ft)
Diameter3.06 m (10.0 ft)
Empty mass33 tonnes (36 tons)
Gross mass273 tonnes (301 tons)
Powered byP241
Maximum thrust7,080 kN (1,590,000 lbf)
Total thrust14,160 kN (3,180,000 lbf)
Burn time140s
PropellantAP, Al, HTPB
Core stage (G, G+, GS) – EPC H158
Height23.8 m (78 ft)
Diameter5.4 m (18 ft)
Empty mass12,200 kg (26,900 lb)
Gross mass170,500 kg (375,900 lb)
Powered byG, G+: Vulcain 1
GS: Vulcain 1B
Maximum thrust1,015 kN (228,000 lbf) (vacuum)
Specific impulse440s (vacuum)
Burn time605s
PropellantLOX / LH2
Core stage (ECA, ES) – EPC H173
Height23.8 m (78 ft)
Diameter5.4 m (18 ft)
Empty mass14,700 kg (32,400 lb)
Gross mass184,700 kg (407,200 lb)
Powered byVulcain 2
Maximum thrust960 kN (220,000 lbf) (sea level)
1,390 kN (310,000 lbf) (vacuum)
Specific impulse310s (sea level)
432 (vacuum)
Burn time540s
PropellantLOX / LH2
Second stage (G) – EPS L9.7
Height3.4 m (11 ft)
Diameter5.4 m (18 ft)
Empty mass1,200 kg (2,600 lb)
Gross mass10,900 kg (24,000 lb)
Powered byAestus
Maximum thrust27 kN (6,100 lbf)
Burn time1100
PropellantMMH / N2O4
Second stage (G+, GS, ES) – EPS L10
Height3.4 m (11 ft)
Diameter5.4 m (18 ft)
Empty mass1,200 kg (2,600 lb)
Gross mass11,200 kg (24,700 lb)
Powered byAestus
Maximum thrust27 kN (6,100 lbf)
Burn time1170
PropellantMMH / N2O4
Second stage (ECA) – EPS ESC-A
Height4.711 m (15.46 ft)
Diameter5.4 m (18 ft)
Empty mass4,540 kg (10,010 lb)
Gross mass19,440 kg (42,860 lb)
Powered byHM7B
Maximum thrust67 kN (15,000 lbf)
Specific impulse446s
Burn time945s
PropellantLOX / LH2
[edit on Wikidata]
Ariane 5
Ariane 5 ES with ATV-4 on board on its way to the launch pad
FunctionHeavy launch vehicle
ManufacturerAirbus Defence and Space for
ESA and Arianespace
Country of origin
20 ESA member states
Size
Height46–52 m (151–171 ft)
Diameter5.4 m (18 ft)
Mass777,000 kg (1,713,000 lb)
Stages2
Capacity
Payload to LEO (260 km (162 mi) circular, 51.6˚)
MassG: 16,000 kg (35,000 lb)
ES: over 20,000 kg (44,000 lb)[9]
Payload to GTO
MassG: 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
FamilyAriane
Launch history
StatusActive
Launch sitesGuiana Space Centre ELA-3
Total launches85
(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 flightG: 4 June 1996
G+: 2 March 2004
GS: 11 August 2005
ECA: 11 December 2002
ES: 9 March 2008
Last flightG: 27 September 2003
G+: 18 December 2004
GS: 18 December 2009
Notable payloadsRosetta
Automated Transfer Vehicle
Herschel Space Observatory
Planck
Boosters (G, G+) – EAP P238
No. boosters2
Height31.6 m (104 ft)
Diameter3.06 m (10.0 ft)
Gross mass270 tonnes (300 tons)
Powered byP238
Maximum thrust6,650 kN (1,490,000 lbf)
Total thrust13,300 kN (3,000,000 lbf)
Burn time130s
PropellantAP, Al, HTPB
Boosters (GS, ECA, ES) – EAP P241
No. boosters2
Height31.6 m (104 ft)
Diameter3.06 m (10.0 ft)
Empty mass33 tonnes (36 tons)
Gross mass273 tonnes (301 tons)
Powered byP241
Maximum thrust7,080 kN (1,590,000 lbf)
Total thrust14,160 kN (3,180,000 lbf)
Burn time140s
PropellantAP, Al, HTPB
Core stage (G, G+, GS) – EPC H158
Height23.8 m (78 ft)
Diameter5.4 m (18 ft)
Empty mass12,200 kg (26,900 lb)
Gross mass170,500 kg (375,900 lb)
Powered byG, G+: Vulcain 1
GS: Vulcain 1B
Maximum thrust1,015 kN (228,000 lbf) (vacuum)
Specific impulse440s (vacuum)
Burn time605s
PropellantLOX / LH2
Core stage (ECA, ES) – EPC H173
Height23.8 m (78 ft)
Diameter5.4 m (18 ft)
Empty mass14,700 kg (32,400 lb)
Gross mass184,700 kg (407,200 lb)
Powered byVulcain 2
Maximum thrust960 kN (220,000 lbf) (sea level)
1,390 kN (310,000 lbf) (vacuum)
Specific impulse310s (sea level)
432 (vacuum)
Burn time540s
PropellantLOX / LH2
Second stage (G) – EPS L9.7
Height3.4 m (11 ft)
Diameter5.4 m (18 ft)
Empty mass1,200 kg (2,600 lb)
Gross mass10,900 kg (24,000 lb)
Powered byAestus
Maximum thrust27 kN (6,100 lbf)
Burn time1100
PropellantMMH / N2O4
Second stage (G+, GS, ES) – EPS L10
Height3.4 m (11 ft)
Diameter5.4 m (18 ft)
Empty mass1,200 kg (2,600 lb)
Gross mass11,200 kg (24,700 lb)
Powered byAestus
Maximum thrust27 kN (6,100 lbf)
Burn time1170
PropellantMMH / N2O4
Second stage (ECA) – EPS ESC-A
Height4.711 m (15.46 ft)
Diameter5.4 m (18 ft)
Empty mass4,540 kg (10,010 lb)
Gross mass19,440 kg (42,860 lb)
Powered byHM7B
Maximum thrust67 kN (15,000 lbf)
Specific impulse446s
Burn time945s
PropellantLOX / LH2


Falcon 9 edit

Side by side comparison
{{Infobox rocket}}{{Infobox rocket/sandbox}}
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.
FunctionOrbital launch vehicle
ManufacturerSpaceX
Country of originUnited States[10]
Cost per launch$61.2M[11]
Size
Height70 m (230 ft) with payload fairing[12]
Diameter3.66 m (12.0 ft)[10]
Mass541,300 kg (1,193,400 lb)[10]
Stages2[10]
Capacity
Payload to LEO13,150 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
StatusActive
Launch sitesCape Canaveral SLC-40
Vandenberg SLC-4E[11]
Total launches3
Success(es)3
Landings2
First flight22 December 2015
Orbcomm OG2 Flight 2
First stage
Engines9 Merlin 1D[10]
Thrust6,806 kN (1,530,000 lbf)[10]
Specific impulseSea level: 282 s[15]
Vacuum: 311 s[16]
Burn time162 seconds[10]
Propellantsubcooled LOX/chilled RP-1[17]
Second stage
EnginesMerlin Vacuum (1D)[10]
Thrust934 kN (210,000 lbf)[18]
Specific impulseVacuum: 348 s[10]
Burn time397 seconds[10]
PropellantLOX/RP-1
Destroyed before launch1
[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.
FunctionOrbital launch vehicle
ManufacturerSpaceX
Country of originUnited States[10]
Cost per launch$61.2M[11]
Size
Height70 m (230 ft) with payload fairing[12]
Diameter3.66 m (12.0 ft)[10]
Mass541,300 kg (1,193,400 lb)[10]
Stages2[10]
Capacity
Payload to LEO13,150 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
StatusActive
Launch sitesCape Canaveral SLC-40
Vandenberg SLC-4E[11]
Total launches3
Success(es)3
Landings2
First flight22 December 2015
Orbcomm OG2 Flight 2
First stage
Engines9 Merlin 1D[10]
Thrust6,806 kN (1,530,000 lbf)[10]
Specific impulseSea level: 282 s[15]
Vacuum: 311 s[16]
Burn time162 seconds[10]
Propellantsubcooled LOX/chilled RP-1[17]
Second stage
EnginesMerlin Vacuum (1D)[10]
Thrust934 kN (210,000 lbf)[18]
Specific impulseVacuum: 348 s[10]
Burn time397 seconds[10]
PropellantLOX/RP-1
Destroyed before launch1

References edit

  1. ^ http://www.astronautix.com/lvs/soyuzu.htm Astronautix.com
  2. ^ Mark Wade (26 March 2001). "Soyuz 11A511U". Friends and Partners.
  3. ^ a b Krebs, Gunter. "Soyuz-U (11A511U)". Gunter's Space Page. Retrieved 2016-04-02.
  4. ^ Krebs, Gunter. "Soyuz-U Fregat (11A511U)". Gunter's Space Page. Retrieved 2016-04-02.
  5. ^ 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.
  6. ^ a b c "Soyuz-U User's Manual" (PDF). Starsem. Retrieved 11 March 2016.
  7. ^ "Конструкция разгонного блока "Фрегат"". NPO Lavochkin (in Russian). Retrieved 10 March 2016.
  8. ^ "IKAR Upper Stage". TsSKB-Progress. Retrieved 21 December 2015.
  9. ^ "Ariane 5 ES". ESA. Retrieved 27 August 2014.
  10. ^ a b c d e f g h i j k "Falcon 9". SpaceX. Retrieved 28 September 2013.
  11. ^ a b c "Capabilities & Services". SpaceX. Retrieved 28 September 2013.
  12. ^ 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.
  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.
  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.
  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.
  17. ^ Elon Musk [@elonmusk] (December 18, 2015). "-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.
  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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